Space Cassette

Rectangular payload bay of my rocket Blade can carry Cassette like independent modules which can attach to each other to create multi staged space ship for deep space missions. With LEO assembled space ships, the duration of energy intense space missions can be shortened and the payload can be increased. A launch from surface of the earth would require really big rockets which would be hard to build and launch.

The cassette based modular design I propose, allows much smaller and fast to launch rockets to build a high energy rocket in orbit. The flexibility due to modularity allows many complex missions to be planned and implemented in short order. At the moment, each mission requires new deep space rocket to be developed.

Some of the cassette modules that can be used to build a high energy rocket in orbit: The modules that provide pure thrust, communication and solar power module, destination specific payload carrying module (such as a folded rover). Each cassette would be attached to one other by polarity controlled magnetic latches. The docking would be achieved by micro thrusters positioned at the back of each module. The aft section of the module where the unified engine is placed would have dead space on its sides. This space would be utilized to place this thrusters and magnetic latches. The mechanically controlled magnets would require zero power to keep the modules attached. Orienting the magnets to achieve opposite polarity would attach the modules and orienting the same polarity would detach the modules. Distributing the thrust over multiple stages yield higher effective thrust while the depleted module would be ejected and lower the weight of the ship.

The thruster modules of the deep space rocket would gradually increase the orbital speed with much less stress on the payload. Once the escape velocity is reached, relevant trajectory injection burn would be triggered. Micro staging would allow efficient generation of thrust depending on the mission. It’s like the multiple artillery propelling charges used depending on the range and the shell.

Perfecting modules and assembling them one after the other depending on the mission would allow way economical and rapid deep space exploration.

Space Loupe

One may thing that flat satellites can only be good for communication. However, if make some research on flat telescopes we can find designs that can be implemented on a foldable satellite.

The Modified Dall–Kirkham telescope uses an elliptical primary and spherical secondary mirror as in the conventional Dall-Kirkham configuration, but also includes a lens group ahead of the focal point to improve off-axis image quality.

This design can be enhanced to be deployed on a foldable satellite. The result would resemble a Loupe. That’s why I called it a Space Loupe. I thought of this design mainly for earth surveillance applications. Where the source is way brighter than the location of the satellite in orbit. Negating the need for light blocking exterior and simplify the design. This design can also be used to observe the Moon and the Solar System which have higher brightness levels and require less magnification. Having more telescopes that cost less and easy to maintain has some potential besides the sophisticated ones. More observation points are obviously beneficial for the science and the national security.

Future of Space Is Flat

My Blade rocket with its high aspect ratio wing design has rectangular box shaped payload bay. Thanks to its hexagonal inner structure. This allows almost 100% space allocation for the orbital payload. Current cylindrical payload bays with conical nose have considerable volumetric loss. On the other hand, there is a trend of flat satellites thanks to Starlink pioneering the way. My rocket would provide a perfect fit for such satellites.

I had written about standardization of satellites on my earlier articles. Now I want to emphasize it further. The rockets, like the buildings are designed from top to bottom. When we have standardized dimensions of satellites, it would give the rocket designer a clear path to design their rockets. Multibillion-dollar rocket design process is by no means standardized and is very inefficient. What enabled the humanity to rapidly increase the global trade and its efficiency was the standardization of the cargo, the shipping containers. Once the payload was clearly defined, companies designed trucks, semi-trucks, trains and the ships accordingly. The system was very efficient.

Flattening the satellites opened up the way for such standardization. Standardized measures should be defined for such satellites clearly defining the height, width and length. Multiples of these dimensions would be the defining measure for the satellite designers and would base their design on these restrictions. The rocket designers start designing their rockets based on these standardized payloads.

I recommend the nations who are investing on the space race but lacking behind the leader should unite and define such standards to improve their efficiency to be able to properly compete.

Unified Engine Design

In the heart of my Blade Rocket and the LNG VTOL Plane lie my Patented unified engine. It is pressure fed in my rocket. It is fed with small, low temperature turbopumps in my LNG VTOL Plane design.

It is a unified monolithic structure composed of Tesla valve, combustion chamber and the aerospike nozzle. All printed in one piece inside a 3d printer. The printer’s building volume determines its dimensions. It would be a parametric design that can be scaled up or down depending on the requirements.

Tesla valve ensures one way flow of propellant from the tanks to the engine. The liquid exiting the valve enters the regenerative cooling canals of the combustion chamber and the aerospike nozzle. These canals are also designed in gradient hexagonal structure. This increases the surface area that the liquids can soak heat from. More importantly, it allows a stabilized pressure chamber with lower weight. As the gas builds more pressure, it increases the strength of the structure which allows higher combustion pressure. The preheated propellant than enters the combustion chamber in gas form ready to ignite. Ideally, once the fuel and the oxygen enter the combustion chamber, they would be at an auto ignition temperature. Negating the need for igniters. The exhaust gas would then be ejected from the aerospike nozzle.

Unified design reduces the path and points of failures for the liquid propellent on its path to the exhaust nozzle.

The tesla valve allows higher pressure on the combustion area compared to the pressure of the propellant tanks. Tesla valve creates a pulsating combustion which increases the combustion efficiency compared to constant fed systems. It also pulsates the exhaust gas which allow high efficiency after burner and augmented air effect. Parametric 3d print nature of the design allows different tesla geometries to be incorporated in design. This produces different pulsation frequencies. Instead of engines resonate, they create a white noise like vibrations. Additionally, gradient honeycomb combustion chamber with pressurized gas absorbs most of the vibrations before they are transmitted to the body of the rocket.

Blade Hexagonal Structure

I named my rocket as Blade. Now on I will reference it as Blade. In this article, I would like to clarify my Patented monolithic gradient hexagonal structure. The load bearing and support of this high aspect ratio rocket was made possible by two things: gradient honeycomb design and pressurized propellent. Gradient honeycomb distributes the load over a larger volume which is a good thing for a lifting body, to have more surface area for lift. The gradual increase of diameter of the hexagons allows well balanced load and pressure distribution. These small voids allow smooth pressure difference transition between the 600 psi fuel tanks and the ambient atmosphere down to vacuum. The void sections facing the belly of the rocket are filled with pressurized methane gas (not up to 600 psi but lower). They soak heat from the belly of the rocket during Mach speeds and used as cold gas thrusters to maneuver the rocket in vacuum and steer it during its return flight. Each hexagonal structure that is filled with liquid methane and liquid oxygen is directly go to the aft engines. They feed the relevant unified engine directly. No piping required. The fuel distribution between the hexagonal reserves is also managed at the aft section of the rocket. Minimizing the piping and complexity.

The hexagonal structures double as structural support, fuel tank and pipe. The pressure of the propellent coupled with this structure strengthens the whole body. Weight induced to keep propellent under pressure allowed the rocket to be shaped as a wing (which requires much more structural support than a pencil shaped rocket). The solution to use honeycomb design allowed pressurized inner structure which added strength without additional weight. This self-supporting architecture allowed a lighter solution for the problem and turned the rocket into a reusable space ship. By allocating some of these hexagonal structures for the by pass air added almost no additional weight penalty but tremendously improved the fuel economy. Additionally, the bypass ducks at the nose reduced the shock waves on the nose to acceptable level.

Finally, and most importantly, such a high aspect ratio structure traveling at very high supersonic speeds could only stay in one piece if the thrust was distributed evenly on its structure. Pressure fed small unified engines allowed very precise throttling with minimal leg time. Only, fast and precise response of the engines could achieve that, not the classical turbopump engines.

İbrahim's Rocket

Let me explain my patented rocket design. It started with a totally different perspective than traditional rockets. If you read my old articles, you would see the roots of the idea. I said to myself. I want to design a rocket that utilizes air’s lifting capacity and the bypass efficiency of the turbofan engines. That required the rocket to have wings and air augmentation. After several iterations I found the solution. Adding wings was just dead weight. Unlike a traditional plane the rocket is full of propellant. This turns it into a brick. The wings would just snap off. The next best thing was to reshape the rocket. The final shape was a surf board design with a wider frontal area with slightly curved front. This has the strength and surface area. It also curves towards the rear to direct the air attached to the surface to be utilized as the augmented air. Just choosing the right geometry, solved both problems at the same time. This design has a considerably weight penalty. How I solved it.

Dual purposing is like diluting the problem so that it has less effect. My orthodox design approach required all the features to be at least dual purposed to keep the idea feasible. That is something I am good at. I utilized the added support weight of the rocket to my advantage. I proposed the interior of the rocket to be gradient hexagonal monolithic lattice. This is the lightest support which is well distributed. I thought of using pressure fed rocket instead of turbopumps. The lateral structures would house the tanks. This increased the volume utilization for fuel storage compared to traditional rocket tanks. The liquid methane and LOX tank strips side by side. While the gradient hexagonal structure maintained the pressure support, the internal walls could be thinner due to minimal pressure difference inside. The dead weight of the wing structure was now supporting the pressurized liquid propellant tanks (Patented dual purposing). The internal structure was not just straight walls going from top to bottom, but had Tesla valve like structures on their way. Just curving the line appropriately added these features. Almost no additional weight needed. It solved the sloshing problem of the liquid propellant, it acted as a horizontal support to the vertical structure and allowed one way flow towards the engine (in case of a puncture, the fuel does not leak easy).

Pressure fed system allowed unified engine block. Tesla valve to allow one way flow, the combustion chamber and the aerospike nozzle. Printed as a unified structure with regenerative cooling canals embedded. The pressure of the propellants would be 600 psi. This allows the engine to operate at around 400 psi. However, pre heating of the propellant would ensure even higher pressure inside the combustion chamber. 3d printing allows almost perfect cooling performance. Therefore, the unified engine block can be printed using Al-Sc alloy strengthened by heavy PEO coating. The whole structure of the rocket would be 3d printed from Al-SC and PEO treated. The internal structure combined with Aluminum would make the rocket a giant heatsink. The internal propellent would be kept at the ideal pressure without wasting the combustion chamber heat. Atmosphere does the heating for free. Separate fuel reserves will also allow the pressure to be kept ideal for the best thrust performance.

By utilizing a pressure fed system, the rocket becomes 0-100% throttleable. The responsiveness would be also very fast negating the need for gimbaled nozzles or any other rudder system. With traditional turbopump rockets you cannot achieve perfect differential throttling.

The wing shape of the rocket reduces the engines’ maximum thrust requirement. Traditional rockets require T/W over 1 to be able to take off vertically. The wing lift capacity of my rocket lowers this number below 1. This reduces the weight of the engine block further.

Let’s come to the air augmentation part of the design. Large surface area curved to direct the air attached to the surface towards the aft section of the rocket has several benefits. Traditional rockets’ flat rear creates a vacuum effect due to sudden stop of air flow from the sides. My design has no such penalties. Air flows perfectly from the nose to the rear. The fuels in rockets are fuel rich burned to lower the combustion chamber temperature. I utilize it to my advantage. The oxygen rich augmented air would act like an afterburner for my rocket. Generating thrust boost for free. Coupled with the non-oxygen part of the air generating by pass air thrust. The overall Isp of my rocket is multiplied on the lower atmosphere. At higher speeds the engine works like a ramjet engine. This immense thrust boost counter balances al the weight penalties. Traditional rocket calculations are made as if they would only operate in vacuum. Therefore, if a rocket has low fuel to weight ratio, it is called a brick. However, my augmented air afterburner is like a virtual fuel for me (I don’t need to carry as much oxygen). Coupled with the lift advantage of the wing design which reduces the weight virtually. Now my rocket has much better fuel to weight ratio. To utilize the maximum benefit of the lower atmosphere, my rocket would have a much flatter flight trajectory on the lower atmosphere and gradually attain altitude. Thanks to the wing shape, most of the thrust can be directed to horizontal speed gain to reach the orbital velocities not to counteract the gravity (that is the main objective of any rocket).

The wing shape has other benefits when it comes to retrieving the rocket stages back. Given that the first stage also has an aerodynamic wave riding nose after stage separation (The gap between the first and the second stage would be filled by a special gasket to keep the rockets aerodynamic profile. After separation this section would be burned out. Because the second stage would fire its engine while still attached to the first stage. This burn will sublimate the gasket.). The wing shaped first stage would than glide toward the landing airfield. There, an electric trailer would catch it and slow it down. The stall speed of empty first stage would be very low. Very small amount of fuel reserve will be used for control authority. Much safer and less stress bearing recovery compared to VTOL rockets. The wave riding shape of the rocket allows it to dissipate its energy more gradually with less heating and much less stress. The first stage would be landing an airfield some distance away from the original. There it would be refueled and relaunched for a home ride. No need to keep the return fuel if you can service it on the ground.

The second stage with the same geometry would be skipping the upper atmosphere and dissipate its energy gradually before reaching the thicker atmosphere. The glider like design would allow gradual and less stress bearing return flight unlike the space shuttle. It may still have some fuel in reserve to further slowdown to minimize the heat build-up. This additional fuel coupled with the ideal heatsink design of the rocket negates the need for heat tiles which is the major point of failure on orbital return flights. As a result, both stages can be safely recovered with minimal depreciation. Much faster refurbishment is possible which further reduces the cost of operation.

The Innovation: Resonant Quantum Gating

The Thermal Paradox

As AI workloads transition from traditional inference to massive-scale training (TPU/GPU clusters), thermal management has become a “energy-negative” bottleneck. Conventional liquid and air cooling are purely dissipative; they consume secondary power to move waste heat. This paper proposes a radical departure: Gated Monolithic Tunneling (GMT).

The Innovation: Resonant Quantum Gating

The GMT architecture utilizes a solid-state monolithic structure integrated at the System-in-Module (SiM) level. Unlike passive thermoelectric generators, the GMT uses an Active Gate controlled by an LC-Resonant Circuit.

Lossless Control: By utilizing the gate’s inherent capacitance within a resonant AC tank, the system maintains a tunneling potential with near-zero energy dissipation.

Maxwell’s Demon Realized: The gated barrier allows for the selective tunneling of high-energy ballistic electrons while remaining opaque to thermal phonons, effectively “filtering” electricity out of heat.

Dynamic Throttling & System Integration

A core feature of the GMT is its Software-Defined Controllability. By modulating the resonance frequency in the MHz range, the GMT can be throttled in real-time to match the transient spikes of modern AI accelerators.

At Peak Load: The system opens the quantum barrier to maximize heat-to-electricity conversion (targeting ~90% Carnot Efficiency).

At Idle: The system throttles down, maintaining thermal equilibrium without unnecessary power draw.

Conclusion

GMT transforms the data center from a heat-producing cost center into a regenerative energy ecosystem. By recapturing up to 80% of waste heat and converting it into a secondary DC power bus, GMT offers the only viable path to 100% Carbon-Free Energy (CFE) targets in the era of the AI boom.