I am perfecting my Blade rocket almost every day to improve its strengths and eliminate its weaknesses. The latest iteration of my rocket is sleeker. It resembles a stingray but with a very high aspect ratio. The center section would be housing the payload bay and would be thicker than the edges to improve passive stability. The very high aspect ratio improved the Lift / Drag ratio and reduced the effect of supersonic shock waves.
The most critical design change came from the engines. The unified engine nozzles are now linear instead of distinct point sources. With the latest update, the exhausts of the rocket look like a dashed line. This setup virtually extends the wing span and reduces the vacuum suction effect on the tail. Linear thrust would have less stress on the high aspect ratio structure compared to the point source thrusters. Well-designed unified engines would reduce the gap between the dashes and the total thrust would look like a continuous line. This would enhance the virtual wing effect and the lift.
The lower profiled design also removed the voids that covered the rocket from nose to tail. Instead, the augmented air is only provided by the air flow at the belly of the rocket and its top section. The result is the reduction of the augmented air, but the reduced drag and weight offset the lost gain.
The latest iteration of Blade; improves structural strength, lowers overall weight, lowers stress level due to thrust inequalities, lowers fuel (down to 10 bar from 600 psi) and combustion chamber pressures (30-35 bar). Additionally, this sleeker design would experience less stress on its return journey from the orbit. Overall improving the mission success rate.
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