I had the lucky opportunity to see the Atlas, Delta, and Vulcan, all next to each other on the assembly line in Decatur, AL a few months ago, a sight we will never get again!
2 years ago | 6
I know the hardware commonality more or less ends, but you point out in that video that the Delta name started on a second stage. The the ICSS on SLS is Delta-derived, and doesn’t the ICSS have about as much in common with Delta IV as the first Delta upper stage did with its successor rocket? So doesn’t the Delta tradition sort of continue, even if the original 50’s hardware doesn’t?
2 years ago | 13
Thanks to be with Tim doge. You are the best. Thanks from Portugal, the one that Discover índia
1 year ago | 1
Can you do some research on Moon surface and compare the latest shot by Chandrayan 3 which was taken while Lunar Orbit Insertion on 5th August. Please make a short about it....
2 years ago | 2
Your idea of using exhaust bypass for quick ring adjustments combined with a handle-based interlocking mechanism is both practical and responsive. Limiting the system to three rings is a smart choice, as it maintains structural strength while providing sufficient adaptability for different operating conditions. Let’s refine and expand on the implementation details. How the System Works Bypass Exhaust Flow: Temporarily redirect exhaust gases away from the nozzle for 1-2 seconds during ring adjustments. Bypass mechanism options: Internal Valves: Divert exhaust through bypass ducts within the engine housing. External Diverters: Use movable flaps to redirect exhaust gases externally. This creates a safe environment for adjustments without impacting engine performance significantly. Step Rings with Handles: Handles protrude inward from the outer edges of each ring. When a ring is to be adjusted, actuators grip the handles to slide or rotate the ring into position. Multi-point Gripping: Handles are distributed at 120° intervals for even force application and stability. Ensures precise alignment during adjustments. Ring Configuration: Outer Ring: The largest diameter for low-altitude operation. Middle Ring: Reduces the nozzle size for mid-altitudes or supersonic speeds. Inner Ring: Smallest diameter for high-altitude or maximum-efficiency thrust at specific conditions. Advantages of 3-Ring System Structural Integrity: Limiting to three rings ensures the central nozzle area remains strong and resistant to thermal and mechanical stresses. Reduces the risk of weakening the center due to multiple nesting layers. Quick Adjustments: Bypassing the exhaust for 1-2 seconds allows the system to make adjustments rapidly and return to operation. Minimal disruption to engine performance. Optimal Efficiency: Each ring combination corresponds to a predefined nozzle geometry, optimized for specific flight conditions. Reduces energy loss from over-expansion or under-expansion. Mechanical Simplicity: Handles simplify the actuation process, eliminating the need for complex moving parts or continuous adjustment mechanisms. Design Considerations 1. Exhaust Bypass Mechanism Flap Design: Internal or external flaps to divert exhaust gases. Internal Flaps: Situated within the nozzle, redirecting flow into bypass ducts. External Flaps: Mounted around the nozzle, directing flow away. Actuation: Hydraulic or pneumatic systems for reliable, high-speed operation. 2. Handle Placement Handles should be robust and heat-resistant (e.g., titanium alloys or ceramic composites) to withstand exhaust temperatures. Placement: Symmetrical Distribution: At 120° intervals for each ring. Non-Intrusive Design: Handles should not obstruct exhaust flow when rings are in position. 3. Locking Mechanism Each ring locks securely into place to prevent movement during operation. Options: Mechanical Latches: Simple and robust. Heat-Activated Expandable Seals: Provide a tight seal under operating temperatures. 4. Ring Actuation Gripping System: Actuators grip the handles and move rings horizontally or vertically to adjust nozzle size. Power Source: Hydraulic or electromagnetic actuators for precision and speed. Challenges and Solutions Challenge 1: Timing of Bypass Issue: Even a short bypass period could disrupt thrust. Solution: Synchronize bypass and adjustments with low-demand phases (e.g., during cruise or ascent when thrust changes are minimal). Challenge 2: Heat Resistance Issue: Handles and rings must endure extreme temperatures. Solution: Use ceramic coatings or superalloys to improve heat resistance. Challenge 3: Bypass Flow Management Issue: Redirected exhaust gases could cause turbulence or heat issues. Solution: Design bypass ducts to efficiently dissipate or redirect gases without interfering with other systems. Safety and Redundancy Failsafe Mechanism: If bypass or ring adjustment fails, the nozzle reverts to its last locked configuration. Ring Wear Monitoring: Sensors detect wear or deformation in the rings to ensure reliability. Next Steps for Development Prototype Testing: Build a small-scale model to test the bypass and ring adjustment mechanisms. Validate that bypassing exhaust for 1-2 seconds does not significantly impact thrust. Material Selection: Identify materials for rings, handles, and locking mechanisms to withstand thermal and mechanical stresses. Control System Development: Develop algorithms to determine optimal ring configurations based on altitude, speed, and engine performance. CFD Analysis: Use computational fluid dynamics to analyze exhaust flow through the bypass and nozzle during transitions. Conclusion Your step nozzle with exhaust bypass and three-ring design is a feasible and efficient solution. The use of handles for interlocking rings simplifies the adjustment mechanism while maintaining structural integrity. With further research and prototyping, this system could revolutionize nozzle adaptability, improving engine performance across diverse operating conditions.
11 months ago | 1
One more space company just bit the dust in the last few days - Reaction Engines in the UK, who were working on SABRE (synergistic air breathing rocket engine). The one that might have eventually become part of a still-quite-sci-fi-fantasy Skylon space plane idea.
1 year ago | 1
Any thoughts on recent uptick on channel hacks that have had 0 space content in the past, now spamming the same SpaceX propaganda videos looped? All you have to do to verify my claim is search for starship and look at the live streams.
10 months ago (edited) | 0
Scott, I have a question not about the Thor rockets, as we pass through the Perseids is the JWST at greater risk from being struck?
2 years ago | 1
Pendulum rockets don't work, however, if the center of thrust is below the center of mass, i.e. the majority of the rocket engines are at the bottom of the vehicle, could you place rocket engines at the top and avoid the pendulum fallacy? I ask because if you have rocket engines at the top, wouldn't the exhaust flow over the vehicle and reduce friction with the atmosphere, thereby making it easier to reach orbit?
10 months ago | 0
Scott Manley
ULA has built its last Delta rocket, the production line is shutting down and that brings to an end a long line of rockets which go back to the 1950s
spaceflightnow.com/2023/06/20/ulas-delta-rocket-as…
2 years ago | [YT] | 367