Flight Mission Research Articles

Analysis of trans‐domain motion process of bullet‐shaped trans‐domain amphibious vehicle

AbstractA fully functional prototype of a bullet‐shaped trans‐domain amphibious vehicle with the ability to perform reciprocating cross‐medium movements has been developed. Once the bullet‐shaped underwater vehicle completes its designated underwater tasks, upon reaching a suitable location for surface observation, it will transform into a bullet‐shaped coaxial counter‐propeller aircraft to carry out cross‐domain out‐of‐water and performing aerial flight missions. The successful transition of the vehicle into amphibious mode is attributed to the design of an innovative energy attitude multiplexing mechanism. Simultaneously, a rational and effective hybrid‐switching strategy has been proposed to enhance the reliability of the vehicle's amphibious mode transition. In view of the complex and changeable cross‐domain environment, we have adopted a modular design concept, breaking down the entire cross‐domain movement process into three key phases: air operation flight, transient cross‐domain, and underwater active sailing. Detailed theoretical analysis, algorithm design, and experimental research have been conducted for each phase. This paper proposes and expounds the key design principles, evaluates the performance indicators of key components, and weighs the matching of body dynamics and propulsion performance to ensure that the vehicle achieves the expected performance. Finally, the success of the test at different phases further proves that the vehicle has the ability to achieve complete cross‐domain operation.

Experimental Validation of a Numerical Coupling Environment Applying FEM and CFD

Experimental results for the transient heat transfer characteristics over a flat plate and over a plate with V-shaped ribs were compared to numerical results from a coupling environment applying FEM and CFD. In order to simulate transient effects in the cooling process of engine components during typical flight missions, the temperature and the velocity at the inlet of the channel were varied over time. The transient temperature distribution at the plate was measured using infrared thermography. Five different plate materials (perspex, PEEK, quartz, aluminum, and steel) were considered to investigate the influence of thermal conduction on the heat transfer between solid and fluid depending on the Biot number. The experimental results represent a reference database for a Python-based coupling environment applying CalculiX (FEM) and ANSYS CFX (CFD). The results were additionally compared to numerical results simulating the complete transient conjugated heat transfer with CFD. A good agreement between the numerical and the experimental results was achieved using different coupling sizes at different Biot numbers for the flat plate and the plate with V-shaped ribs.

Control-oriented imitation learning for atmospheric flight control of launch vehicles under wind disturbance

The atmospheric flight control of launch vehicle is required to track the nominal trajectory while obeying path constraints on the aerodynamic load peak. Due to the wind disturbance, wind-induced angle of attack may increase the aerodynamic load peak, and reducing of it will lead to larger trajectory tracking error. Because of the cumbersome tuning of gain schedule and the dependency on accurate wind prediction, it is difficult for existing methods to handle the trade-off problem between reduction of the aerodynamic load peak and trajectory tracking error under uncertain wind disturbance. The presented research is intended to remedy this difficulty through learning based methods. The ascent flight phase is modelled as a multiple objective Markov decision process, where the trade-off under wind disturbance is precisely modelled as the optimization of a multi-objective vector under the stochastic state transition. A neural network flight control policy is then trained by a novel control-oriented imitation learning (CoIL) scheme. The CoIL scheme incorporates two control-oriented design within the standard reinforcement learning scheme: the inverse reinforcement learning that infers a proper reward from demonstration trajectories to represent the multi-objective vector of atmospheric flight control, as well as the policy hierarchy that simplifies interaction with the high order vehicle dynamics. Compared with previous learning-based attempts in the literature, this scheme uses orders of magnitude fewer demonstration trajectories and avoids hand-programmed reward design. Evaluations are performed under an ascent flight mission, indicating that the obtained policy outperforms the prevalent baseline controllers with reduction of the normalized maximum aerodynamic load by 28.3%, altitude error by 38.6%, velocity error by 17.1% and path angle error by 42.7% under unpredicted wind disturbance.

Evaluating the Accuracy of UAV and TLS for 3D Indoor Modelling in Large-Scale Building Environments

The accuracy of 3D indoor reconstructed models is critical in various applications such as indoor navigation, virtual reality (VR), and building information modelling (BIM). This research study aims to evaluate the accuracy of Unmanned Aerial Vehicles (UAV) and Terrestrial Laser Scanning (TLS) for 3D indoor modelling in large-scale building environments. To achieve this, several evaluations were made towards the number of point clouds, estimated costs and accuracy of the 3D indoor reconstructed model generated from dense point clouds acquired by Unmanned Aerial Vehicle (UAV) and Terrestrial Laser Scanner (TLS). A small indoor classroom was selected for this study approximately 100m2. In UAV data acquisition, three (3) flight missions were set up at the front, left and right views. Meanwhile, five (5) scanning stations were placed on-site for the TLS method. Due to various different flight mission views in the UAV dataset, the number of point clouds was quite higher compared to the TLS method. However, a better-quality visualization of the TLS model has been obtained as opposed to the UAV 3D model. For the required time to generate a 3D model, it showed that UAV processing time was more consuming lots of time than the TLS method, especially when georeferencing the overlapping photographs. In terms of accuracy, the RMSE value from TLS was better than UAV at 0.003m compared to UAV at 0.021m. Overall, this study provides insights into the accuracy and suitability of UAV and TLS for 3D indoor modelling in large-scale building environments. The results can inform decision-making processes in various industries such as architecture, engineering, and construction, where accurate and reliable 3D models are crucial for design, planning, and management purposes.

Unmanned Aerial Vehicles: The Possibility of Using Fuel Cell, Battery, and Turbocharger Technologies

The adverse impacts of fossil fuels on the environment have guided the authorities to set the official 100% phase out target for sales or registrations of new internal combustion engines (ICEs) that use fossil fuels as the prime mover. Batteries and fuel cells have proved to be an appropriate alternative for the ICEs to be used in cars, trucks, and buses. Although there have been limited number of studies to use batteries as the prime mover of small size planes, the possibility of using the integrated system of battery and fuel cell is yet to be investigated in the airplane industry.Due to the infancy of using batteries and fuel cells in airplane sector, the studies are limited to the domain of Unmanned Aerial Vehicles (UAVs). UAVs are designed to fulfill long and high-altitude flight missions. The flight duration and flight altitude have been proved to be improved using the proton exchange membrane fuel cells (PEMFCs) as the prime-mover of the UAVs. However, the low acceleration of the PEMFCs has triggered the idea of integrated PEMFCs and Lithium-Ion (Li-ion) battery. Thus, the integrated system can improve the low range of batteries by maintaining high acceleration and fast re-fueling time.Among different types of fuel cells, PEMFCs are established to be the best option for mobility applications, and the well-known Nickel Manganese Cobalt (NMC), and Lithium Titanite Oxide (LTO) Li-Ion batteries are considered as the most efficient types. LTO enjoys from the highest performance, lifespan, and safety by higher costs, whereas NMC provides acceptable performance with low costs and high specific energy.Published results have indicated that PEMFC can be utilized in an UAV, reducing the overall weight and leading to the longest flight endurance. However, better acceleration and simpler configurations can be achieved by Li-Ion battery packs, although the practical implementation is still limited by the actual chemistry. So far, it is believed that fuel cells can be suitable for cruise flight while batteries are more appropriate for other flight modes.In addition to the possibility of the integrated battery and fuel cell system to improve the overall performance of the UAVs, the integration of the turbochargers to the PEMFCs is believed to facilitate the transition from engines to more fuel cell/battery technologies. To reach the maximum thrust and minimum fuel consumption rate in an UAV, a hybrid propulsion system of a PEMFC and a single stage turbocharged engines is able to provide the maximum thrust, the minimum fuel consumption rate, and the thermal efficiency of 34.58 mg/s, 69.56N, and 62.41%, respectively.This study evaluates the possibility of integrating the fuel cell technology to the batteries as an alternative for fossil fuel-based combustion engines for the small sized UAV application. To further improve the performance of the UAV, a turbocharger is also integrated to reach higher thrusts and lower fuel consumption rates. The suggested integrated system, which is shown in Fig. 1., is designed to provided 6.8 kW power for a UAV with TWR (Thrust to Weight Ratio) of 0.4 and weight of 17.7kg. PEMFC will be used as the selected type of fuel cell while NMC is the considered type of Li-Ion battery. The turbocharger is also a hydrogen fueled ICE with the compression ratio of 11.15. The goal of this study is the performance evaluation of the current integrated system in an optimized condition considering the size, weight, hydrogen consumption, thrust, and overall efficiency as the output parameters. Figure 1

Bridging the gap: parallel profiling of ribosome associated and total RNA species can identify transcriptional regulatory mechanisms of plants in spaceflight

ABSTRACT As plants are an essential component of sustainable life support systems, long-duration space missions will require a sophisticated understanding of plant adaptations to spaceflight and microgravity. For many years, transcriptional profiling of steady state mRNA abundances has been used as measure of plant adaptations to the space environment. However, measured changes in transcript abundances are often not reflected in corresponding changes in the proteome due regulatory processes governing translation. Translating ribosome affinity purification (TRAP) is a technique which selectively targets ribosome bound mRNAs for isolation and downstream sequencing. Comparing profiles of ribosome associated mRNAs with total mRNAs provides insight into the translatome and may more accurately inform on the cellular responses to the spaceflight environment. Toward that goal, this work describes a methodology developed ahead of the APEx-07 flight mission.

Bimetallic Metal Organic Framework Composites for Carbondioxide Capture

Maintaining breathable air in human space flight missions is a challenge since there will be a gradual increase in the concentration of CO2 due to the exhalation of the spacecraft crew. Modern air revitalization technology for space missions uses temperature swing adsorption with zeolite-based materials as the adsorbent. However, the major drawbacks of zeolites are difficulty in regenerating used adsorbent and low selectivity towards CO2. Besides, frequent replacement of adsorption beds is necessary because of their low adsorption capacity towards CO2. This requires carrying a few spare beds in the spacecraft, which is not preferred because of the low-weight requirements for space missions. Hence, shifting to alternate materials with more selectivity and adsorption capacity toward CO2 becomes essential. Metal-organic frameworks (MOFs) are a class of crystalline materials found to be potential adsorbents for CO2 capture. Due to their ultra-high porosity, tunable pore characteristics, selective capture, and synergistic performance, they could replace the existing zeolite-based adsorbents. Further enhancement in the adsorption capacity could be achieved by introducing a secondary metal into the framework. This will bring heterogeneity in the structure, creation of defects, and open metal sites, thus enhancing the adsorption behavior. Incorporating a secondary metal into the framework and an additional filler material like activated carbon, making a BMOF composite, would lead to an exemplary improvement in the adsorption activity. The addition of filler material will lead to an increase in pore volume, which will enhance the adsorption capacity. In the current work, activated carbon was synthesized from sawdust via chemical activation method using KOH as the activating agent. It was carried out at low temperatures to boost the porous structure formation. Then the composite of Cu-Ni bimetallic MOF with activated carbon was prepared through one-pot solvothermal synthesis. The incorporation of activated carbon created an additional number of pores in the system leading to enhanced adsorption. N2 adsorption-desorption analysis was carried out to find the surface area. The results showed that the surface area of activated carbon and Cu-Ni-Activated carbon BMOF composite was found to be 576 m2/g and 1321 m2/g, respectively. The analysis also revealed the presence of microporous system in the material. Several characterization techniques, such as IR, SEM, XRD etc., were used to study morphology and characteristic features. The SEM shows that the incorporation of nickel and activated carbon have made a profound modification on the octahedral morphology of copper.CO2 adsorption studies were carried out at 1 bar, 25°C. The BMOF composite adsorbent was found to adsorb ~4.52 mmol/g of CO2 whereas the as-synthesized activated carbon and ZSM-5 were found to adsorb ~2.71 mmol/g and ~1.68 mmol/g respectively. To understand the level of microporosity in the supermicropores range, CO2 adsorption analysis at 1 bar and 0°C was carried out since N2 adsorption at -196°C have limitations due to kinetic diffusion related problems at low temperatures. It revealed a micropore volume (<1.066nm) of 0.252 cm3 /g and a pore size range of 4-10 angstroms, which is ideal for selective CO2 adsorption. Also, the BMOF composite was found to adsorb ~8.27 mmol/g at 0°C, which showed that adsorption capacity increases with a decrease in temperature. Hence, the BMOF composites could serve as a promising adsorbent for selective CO2 capture. Figure 1

Statistical Algorithms with Phase-Sensitive Detection for the Number of Hovers and S Turns in Aircraft Flights

Compared to maximum state parameters, such as maximum altitude and Mach, the number of hovers and S turns can be used as process parameters representing the complexity of military aircraft maneuvers when classifying big flight mission data to compile flight load spectra for structures. This study developed intelligent statistical algorithms based on yaw angle data from flight parameters such as the number of hovers and S turns. Using the median-crossing de-redundant function of Phase-Sensitive Detection (PSD) and analyzing the characteristics of 360° hovering flight parameters, a statistical algorithm for the number of hovers during a flight profile is presented. Using the split-half function of PSD, a triangle layering algorithm based on the yaw angle signal was developed to count the number of S turns during a flight profile, where the signal of each sublayer is segmented into median-crossing intervals to eliminate the redundant median-crossing marks from the previous layer. Compared with artificial means, the statistical results of the flight example showed that the developed intelligent algorithms are effective.

Optimization Research on the Heat Transfer Capacity of an Aircraft Fuel Thermal Management System

The thermal management system (TMS) for aircraft fuel is a critical component of integrated TMSs in aircraft. As such, its optimal design is necessary to ensure the efficient completion of flight missions. This study presents the model building of a numerical simulation model for the fuel TMS, with the objective of minimizing fuel return flow. Sensitivity analysis was performed using variance analysis. The genetic algorithm was utilized for the optimization of the model building, taking into consideration the system’s geometric structure and performance parameters, which include the pipe length, the ram air-fuel HX’s efficiency, and the ram air’s volume flow rate in the ram air cooling subsystem, as design variables. The optimization solution for system design variables yielded a design scheme with the highest working efficiency for the fuel TMS. In this paper, the genetic algorithm in AMEsim software is adopted, which can also effectively optimize the design parameters and achieve the optimization objective. Compared with the original TMS structure, the heat dissipation capacity of the fuel TMS is improved and reduced the return fuel flow by 67.4% after the optimization of system structure parameters.

Starting of a scramjet air intake

The starting of a supersonic air-intake at the design Mach number depends on the internal blockage due to flame-holder struts in the combustor. In the present work, the starting of a two-dimensional supersonic air-intake for scramjet operation was verified experimentally on an isolated full-scale truncated model. The first ramp of the supersonic air-intake was truncated and simulated from downstream of the second ramp where the local Mach number was 3.7. The flight mission dictated the opening time of the cowl plate to be fixed as 200 mS. The maximum blockage of struts which allows the intake to start was determined by varying the blockage ratio in the range of 20% to 30%. The results indicate that the intake starts when the blockage ratio was 20%, but unstarts for 25% and 30%. In the unstart condition, discrete frequencies of 45 Hz and 60 Hz occurred and pressure fluctuations in the intake showed limit cycle oscillations. A detailed analysis of unsteady pressure fluctuations confirms that the buzz could be modeled as a Van Der Pol oscillator with nonlinear damping.

Multi-fidelity and multi-objective aerodynamic short nacelle shape optimisation under different flight conditions

AbstractThroughout the course of a flight mission, a range of aerodynamic conditions, including design-point conditions and off-design conditions, are encountered. As the bypass ratio increases and the fan-pressure ratio decreases to reduce the engine’s specific fuel consumption, the engine diameters increase, which results in an increase in the nacelle weight and overall drag. To reduce its weight and drag, a shorter nacelle with a length-to-diameter ratio $L/D = 0.35$ is investigated. In this study, an adaptive cokriging-based multi-objective optimisation method is applied to the design of a short aero-engine nacelle. Two nacelle performance metrics were employed as the objective functions for the optimisation routine. The cruise drag coefficient is evaluated under cruise conditions, whereas the intake pressure recovery is evaluated under takeoff conditions. The cokriging metamodel are refined using an effective infilling strategy, where high-fidelity samples are infilled via the modified Pareto fitness, and low-fidelity samples are infilled via the Pareto front. By combining parameterised geometry generation, automated mesh generation, numerical simulations, surrogate model construction, Pareto front exploration based on the non-dominated sorting genetic algorithm-II and sample infilling, an integrated multi-objective optimisation framework for short aero-engine nacelles is developed. Two-objective and three-objective test functions are used to validate the effectiveness of the proposed framework. After the optimisation process, a set of non-dominated nacelle designs is obtained with better aerodynamic performance than the original design, demonstrating the effectiveness of the optimisation framework. Compared with the kriging-based optimisation framework, the cokriging-based optimisation framework outperforms the single-fidelity method with a higher hypervolume value at the same number of iteration loops.

A comprehensive security and performance assessment of UAV authentication schemes

AbstractIn the past few years, unmanned aerial vehicles (UAVs) have significantly gained attention and popularity from industry, government, and academia. With their rapid development and deployment into the civilian airspace, UAVs play an important role in different applications, including goods delivery, search‐and‐rescue, and traffic monitoring. Therefore, providing secure communication through authentication models for UAVs is necessary for a successful and reliable flight mission. To satisfy such requirements, numerous authentication mechanisms have been proposed in the literature. However, the literature lacks a comprehensive study evaluating the security and performance of these solutions. In this article, we analyze the security and performance of 27 recent UAV authentication works by considering ten different key metrics. First, in the performance analysis, we show that the majority of UAV authentication schemes are lightweight in their communication cost. However, the storage overhead or the energy consumption is not reported by many authentication studies. Then, we reveal in the security analysis the widely employed formal models (i.e., abstract description of an authentication protocol through a mathematical model), while most of the studies lack coverage of many attacks that can target UAV systems. Afterwards, we highlight the challenges that need to be addressed in order to design and implement secure and reliable UAV authentication schemes. Finally, we summarize the lessons learned on the authentication strategies for UAVs to motivate promising direction for further research.

Routine and Safe Operation of Remotely Piloted Aircraft Systems in Areas with High Densities of Flying Birds

Remotely Piloted Aircraft Systems (RPASs), or drones, have had a rapid uptake for scientific applications and are proving particularly valuable for data collection in the natural world. The potential for bird strikes presents a real hazard in these settings. While animal welfare is a primary consideration when planning and executing RPAS operations, the safe operation and return of RPASs is the key to successful flight missions. Here, we asked if RPASs can be routinely and safely implemented to meet data collection requirements in airspaces with high densities of flying birds. We flew quadcopter RPASs over breeding seabird colonies in tropical island settings. A dedicated spotter adjacent to the pilot recorded all interactions between flying seabirds and the RPAS unit while aerial population surveys were being undertaken. Over 600 interactions were recorded for nine species of seabirds. We flew over 100 flights totaling 2104 min in airspace routinely occupied by dense aggregations of seabirds without a single collision. We demonstrate a high capacity to undertake safe and successful RPAS operations in airspaces that contain high densities of flying seabirds. While bird collisions remain possible, such outcomes are clearly rare and should be placed in context with routine disturbances by ground surveys to meet the same objectives. RPASs routinely offer the least invasive method for collecting ecological data compared to traditional field methods and can be undertaken with relatively low risk to the successful completion of the operation.

Aerodynamic Investigation and Simulation Studies on Wing Section of an Unmanned Aerial Vehicle Attached with Solar Plate

The paper investigates the aerodynamic performance and power requirement characteristics of wing sections integrated with high-lift airfoil to support the operation of solar-powered Unmanned Aerial vehicle (UAV). The flight mission is aimed to simulate the operation of solar-powered UAVs under low -speed environment. The research focuses on studying the aerodynamic effect of non-solar UAV wing model and solar UAV wing model for the varying angle of attack. The UAV wing models are tested using a subsonic wind tunnel to validate the aerodynamic characteristics at low-speed condition. The aerodynamic parameters such as coefficient of lift (Cl), coefficient of drag (Cd), coefficient of pressure (Cp), and the total power required to accelerate the solar UAV are studied to maintain steady level flight. The solar UAV and non-solar UAV wing models were subjected to a computational process to examine the pressure and velocity distributions for the aerodynamic performance analysis. Evident results show that the solar cells positioned at the flow separation region of the UAV wing model produces an aerodynamic efficiency rate of 5.45% and required 37.13W of minimum power compared to non-solar UAV at the Reynolds number of 9.8 106.

THE METHODOLOGY FOR STUDYING PILOTS’ READINESS FOR FLIGHT IN THE PROCESS OF COMBAT TRAINING

The article focuses on the readiness of flight personnel for flights. The authors review research works that reflect the need for psychological tracking during the preparation for flights, studying the flight mission, conducting trainings in order to reduce aviation incidents. The “Methodology for Diagnosing the Readiness of Flight Personnel for Upcoming Flights” Прикладные исследования, технологии 85 is presented. The technique is simple in application and data counting, and will be useful for psychologists, deputy squadron commanders for military-political work and flight crew commanders.

Real-time path planning of controllable UAV by subgoals using goal-conditioned reinforcement learning

The conventional path planning problem for an unmanned aerial vehicle (UAV) typically involves a pre-defined environment and mission, with the objective of reaching a single target point. However, in order to perform different missions, the agent must be trained from scratch. In this paper, we propose a new path planning algorithm for UAVs by training them to be controlled by subgoals, which enhances their degree of freedom to perform various maneuvers. The subgoals can be defined by the user and given to the agent in real-time, allowing the UAV to perform diverse flight missions without prior knowledge of the environment. To achieve this, we utilize goal-conditioned reinforcement learning to train the UAV agent to reach various goals by learning different flight maneuvers. In experiments, we designed specific scenarios to test the UAV agent’s ability to perform concrete missions, such as high-flying, low-flying, penetrating, and bypassing. The experimental results show that the same UAV agent trained in a simple environment can accomplish difficult missions in various scenarios. The pre-trained UAV agent can be utilized in other environments as it can be controlled by the subgoals.

Design of a New Multi-Variant Solar Panel Deployment System (Mvspds)

Multi-Variant Solar Panel Deployment System (MVSPDS) is defined as the satellite deployment System which can change its orientation according to the power supply required for the satellite or power supply source available to the satellite. To deploy the solar panels completely, it is necessary to design the deployment mechanism which has high precision and reliability. So, this method of deployment will not only provide the said benefit but also it will allow a wide range of application. Consequently, the analysis on the dynamic characteristic of the deployment mechanism must be done at an initial design stage. The design effectiveness and structural safety of the proposed solar panel module were validated by launch vibration and in-orbit environment tests at the qualification level. In this paper, the complete design of a new Multi-Variant Solar Panel Deployment System in a Satellite is proposed completely by me, where the author have inculcated various deployment methods and proposed a new method of satellite deployment. The complete design is done in the Autodesk 360 software (Educational license) where the design and animation method are extensively used to make this possible. It will be clearly depicted from the design that the structure is very compact during the process of orbit insertion. Yet when it come into working it definitely works according to the power need of the satellite. For an example when the satellite needs less amount of power it will transform itself in such a way that the amount of power generation will be less on the other hand when the satellite needs more power than the Solar Panel will change itself in such a way that it will have the maximum surface area as a result of which the power generation will be maximum. Moreover, the variety which provides is really unique as it also has the power to change its solar panel into different structure for an example it can change itself into a circle like structure it can change itself in the canister to form another structure and moreover it will work completely according to the need if programmed properly for space flight mission. And hence can give rise to a wide variety of different deployment methods.

A Systematic Review of UAV altitude control systems

With the rapid development of informationization and intelligence in modern society, UAVs and their related technologies have been applied and researched on a larger scale, which also poses new challenges to the control accuracy and safety performance of UAV flight control systems. For UAVs, entering the mission area at a certain height and speed for mission flight is the normal state of flight most of the time. Therefore, the altitude control system is the most commonly used flight control method for UAVs, and its design is very necessary at this stage. This paper provides a systematic review of the research progress of UAV altitude control system.

Design of a Direct-Liquid-Cooled Motor and Operation Strategy for the Cooling System

To make an all-electric aircraft possible, both high power densities and efficiencies are needed. However, particularly high demands are also placed on the thermal management system. Often, the electric motor and cooling system are considered without co-optimization. Particularly in the case of electric motors with conductors directly cooled by a liquid, there is great potential for optimization, since the temperature-dependent Joule losses determine the largest part of the losses. This publication shows the main influencing parameters for the electric motor and cooling system: coolant speed and winding temperature. In addition, the influence of the cooling system control during a flight mission is demonstrated and its potential in mass reduction is quantified. It could be shown that with a low utilized electric motor the maximum winding temperature of 130 °C is beneficial, the cooling system should work in almost all operation points in its sized operation and the mass of the heat exchanger and pump is negligible compared to the mass of the electric motor and energy storage.

Design and dry wind tunnel test of progressive flexible variable bending wing

AbstractThe deformable wing structure can change its aerodynamic shape according to the change of flight mission and flight environment, so as to obtain better lift-drag, stability and control characteristics, which is considered as one of the future research directions of aviation technology. Considering the current technology maturity and reliability, a gradient corrugated fin is designed to realise the bending deformation of the wing. The structure of the skin is optimised to keep the skin smooth during deformation. In addition, a progressive push and pull rod is proposed to drive the wing deformation, and the fluid-structure interaction simulation is carried out for the wing deformation. At the same time, the changes of wing aerodynamic characteristics under different angles of leading and trailing edges and different push rod action schemes are analysed. Finally, a dry wind tunnel simulation test of the designed progressive flexible variable bending wing is carried out. The results of fluid-structure interaction simulation and dry wind tunnel test show that the progressive flexible variable bending wing proposed in this paper has a simple and reliable structure and remarkable deformation effect. It has advantages in increasing lift and reducing drag, ensuring high lift-drag ratio and providing wing trim moment. The deformable wing dry wind tunnel test platform designed by this method is structurally reliable, easy to operate, and can accurately reflect the influence of wing deformation on its aerodynamic force, which provides a verification means for the development of the design method and the design of practical aircraft in the future.