Figure 1 Microsatellite appearance structure Three-dimensional microsatellite model with solar panels, antenna, and external components attached to a cubic main body. The three-dimensional microsatellite model shows a cubic main body with 2 rectangular solar panels extending horizontally from ... More about this image found in Microsatellite appearance structure Three-dimensional microsatellite mod...

Figure 2 Microsatellite optimization model parameters Microsatellite optimisation diagram showing structural parameters and grouped subsystem dimensions for antenna, solar wing, and main body. The microsatellite optimisation diagram contains 2 panels. The left panel illustrates the microsatell... More about this image found in Microsatellite optimization model parameters Microsatellite optimisation...

Figure 3 Genetic algorithm programming algorithm flow chart A flowchart showing a satellite component disassembly optimisation process for antenna, solar wing, and main frame modules. The flowchart begins with Start, followed by Initialise global variables. The parameters are racial scale equa... More about this image found in Genetic algorithm programming algorithm flow chart A flowchart showing a...

Figure 4 Optimization process of antenna mass m_r and convergence process of antenna length lr A dual-axis line graph showing convergence of antenna mass and antenna length values across 13 optimisation iterations. The dual-axis line graph displays changes in antenna mass, m r in kilograms, and antenna length, l r in metres, over 13 optimisation iterations. The x-axis is labelled Iterations, times. The left y-axis represents m r values from 0 to 0.5, while the right y-axis represents l r values from 0 to 0.5. The antenna mass decreases sharply from approximately 0.33 kilograms to around 0.11 kilograms before stabilising. Antenna length increases from approximately 0.30 metres to about 0.43 metres and gradually stabilises near 0.40 metres after later iterations. More about this image found in Optimization process of antenna mass m_r and con...

Figure 5 Solar array mass m_b optimization process and design variables convergence procedure Multi-line graph showing optimisation convergence of solar wing mass and dimensional parameters across 31 iterations. The multi-line graph displays optimisation trends for solar wing parameters across 31 iterations. The x-axis is labelled Iterations, times. The left y-axis represents values for m b in kilograms, l b in metres, and b b in metres, ranging from 0 to 2.5, while the right y-axis represents h b in metres, ranging from 0 to 0.01. The m b values decrease from approximately 2.0 kilograms to below 0.9 kilograms before stabilising. The l b values initially decrease and then stabilise around 0.4 metres. The b b values decrease slightly and remain close to 0.2 metres. The h b values increase initially, then gradually decline and stabilise near 0.004 metres during later iterations. More about this image found in Solar array mass m_b optimization process and de...

Figure 6 Main frame mass optimization process and geometric design parameters convergence process Optimisation convergence graphs showing microsatellite mass and structural parameter stability across 13 iterations. The optimisation convergence graphs show microsatellite structural parameter ch... More about this image found in Main frame mass optimization process and geometric design parameters conver...

Figure 7 Testing the effectiveness of genetic algorithms Contour plots comparing genetic algorithm and nonlinear constraint optimisation results for antenna, solar wing, and microsatellite frame parameters. The contour plots compare optimisation results obtained using a genetic algorithm and n... More about this image found in Testing the effectiveness of genetic algorithms Contour plots comparing ...

Figure 8 Optimized fundamental frequency and modal shape Finite element modal shape figures showing microsatellite deformation patterns at frequencies of 31.084 hertz and 34.443 hertz. The finite element models show 2 modal shape analyses of a microsatellite structure with deployed solar panel... More about this image found in Optimized fundamental frequency and modal shape Finite element modal sha...

Figure 9 Optimized schematic diagram of microsatellite structure Comparison of initial and optimised microsatellite internal structural layouts with repositioned subsystem components and solar panels. The schematic diagrams compare the initial and optimised microsatellite structures. Panel A s... More about this image found in Optimized schematic diagram of microsatellite structure Comparison of in...

Figure 1 Morphing aircraft flight sequence Source: Authors’ own work A trajectory diagram showing contraction, extension, and deflection states of a forebody during flight from launch site to target. The trajectory diagram illustrates the flight path of a vehicle from the launch site to the... More about this image found in Morphing aircraft flight sequence Source: Authors’ own work A traject...

Figure 2 Configuration of morphing aircraft Source: Authors’ own work A set of six vehicle configuration diagrams showing contraction, extension, and deflection forebody states in three dimensional and main views. The set of six vehicle configuration diagrams illustrates contraction, extens... More about this image found in Configuration of morphing aircraft Source: Authors’ own work A set of...

Figure 3 Deflection principle Source: Authors’ work A schematic diagram showing refractive index regions and interface angles inside a missile forebody structure. The schematic diagram illustrates refractive index regions and inclined interface geometry inside a missile forebody structure. ... More about this image found in Deflection principle Source: Authors’ work A schematic diagram showin...

Figure 4 Scaled model of the hypersonic slender Source: Authors’ own work A dimensional schematic of a missile body used for verifying numerical calculation effectiveness showing length, body dimensions, and reference point location. The schematic diagram shows the geometric dimensions of a... More about this image found in Scaled model of the hypersonic slender Source: Authors’ own work A di...

Figure 5 Comparisons of L/D, and C p versus α Source: Authors’ own work A set of two scatter graphs comparing experimental and numerical aerodynamic results versus angle of attack. The set of two scatter graphs compares experimental data and numerical approach results for ... More about this image found in Comparisons of L/D, and C p versus α Source: Authors’ ...

Figure 6 Mesh of contraction state Source: Authors’ own work A set of mesh diagrams showing surface and body computational grids around a missile geometry. The set of mesh diagrams illustrates computational mesh generation for a missile geometry. Panel a shows the face mesh applied to the m... More about this image found in Mesh of contraction state Source: Authors’ own work A set of mesh dia...

Figure 7 Pressure contours of contraction and extension state Source: Authors’ own work A twelve-panel pressure contour set showing missile flow fields from Mach 1 to Mach 6 for contraction and extension configurations. The twelve-panel pressure contour set presents computational flow field... More about this image found in Pressure contours of contraction and extension state Source: Authors’ ow...

Figure 8 L/D comparison of contraction state and extension state Source: Authors’ own work A six-panel graph set comparing lift to drag ratio against angle of attack for contraction and extension states from Mach 1 to Mach 6. The six-panel graph set illustrates the lift-to-drag ratio versus... More about this image found in L/D comparison of contraction state and extension state Source: Authors’...