David Ong’s Post

Moving Sentinel-1C to Vega-C's Vampire payload adapter, Image: Moving Sentinel-1C to Vega-C's Vampire payload adapter, : Image: Moving Sentinel-1C to Vega-C's Vampire payload adapter

Aerodynamic forces are generated by the difference in velocity between the rocket and the air.  https://lnkd.in/gHc7hgCQ

The climate control setpoint for the observation level is equal to the anticipated temp of that evenings opening of the enclosure. There is a low rate of temperature changed allowable for that level for the lenses. So the controls and the operation of the hvac for that level need to be robust but responsive.

USC Rocket Propulsion Lab's Aftershock II achieved a record altitude of 470,400 feet, surpassing a 20-year-old record and reaching speeds of 3,602 mph. Launched on October 20 from Black Rock Desert, the rocket employed advanced technologies like custom avionics and titanium fin designs. Ryan Kraemer, leading the project, highlighted the importance of their innovative systems, including thermal protection and onboard computers. Aftershock II's success builds on previous achievements like the Traveler IV, offering valuable flight data. #Rocketry #Recordbreaking #Aerospace https://lnkd.in/gsWtVYm5

Not good. For those unaware, these are fairly large satellites, with a 131 ft wingspan weighting in at around 13,000 lbs: https://lnkd.in/eEPX3tAQ This follows the loss of Intelsat 29e in 2019 due to power anomaly or micrometeoroid strike, marking the second EpicNG (next-generation) Intelsat satellite out of commission: https://lnkd.in/eZ6zmNTC

YASDE! --> active GEO satellite Intelsat 33E (41748 / 2016-053B) breakup U.S. Space Forces – Space (S4S) has reported the breakup of the active geosynchronous Intelsat 33e satellite with an event time of 2024-10-19 04:30 UTC. 20 pieces of #SpaceDebris are reported to be tracked (ref graphic from space-track.org home page). See also U.S. Space Forces – Space (S4S) posting on X: https://lnkd.in/gg_MCPka (x.com URL) The issue was initially manifested as a loss of service by the active satellite --> ref SpaceNews article: https://lnkd.in/gXGZgetx (spacenews.com URL) This is a relatively high piece count for a GEO breakup -- the total count eventually entering the US catalog could be less than 20 -- we'll see. ...and this is more bad news for Boeing, who manufactured the satellite bus -- a Boeing 702MP, which appears to use both biprop and electrical propulsion. Intelsat 33e has been plagued by propulsion issues starting with the 2016 launch. My money is on this being related to the propulsion system.... #LongTermSustainmentOfSpace #SpaceDebris #SpaceSituationalAwareness

2013 to 2025 🛰️ with CubeSats It has now been 12-years since we started designing and building space missions Here is the prototype model for every space mission we have ever worked on

Splashdown of space capsule it is a method of landing ,the capsule land on large body of water the water provide enough cushioning for the capsule to dumb the last amount of kinetic energy and prevents using the breaking rockets like the case in the Russian Soyuz space capsule and the Chinese space capsules or using airbags as is the case with the Boeing Starliner crewed space capsule , that analysis represent space capsule with Apollo space capsule dimensions and weight, the capsule have a diameter of 3.9 m and weight of 5560 kg the splashdown you see occurs with the next conditions : ·      Water entry angle 27.5 ·      Vertical velocity 35 ft/s (10.668 m/s) equivalent of splashdown with only two parachute deployed instead of 3 ·      Horizontal velocity 51 ft/s (15.5448 m/s) I made explicit analysis using ANSYS and by considering the space capsule as rigid body I was interested to study the splashdown from the kinematic point of view the simulation time represent 1 sec of the impact  From the analysis we can found that the capsule lost 50% of its kinetic energy after just 0.1 sec and 75% after just 0.25 sec from the impact with water. The horizontal velocity dropped from its initial value of 15.545m/s to 3.119m/s The vertical velocity dropped from its initial value of -10.668m/s to almost zero in 0.1115 sec then the vertical velocity increase to 5.433m/s at the end of the analysis time due to exchange of momentum from complex interaction between water and capsule The peak acceleration is 137.76 m/s^2 that is 14 g but that for a very short time less than 0.1 sec at the moment of the impact ,with average of 6.9 g for the 1 sec simulation time Just note that the analysis don’t include air resistance I will try next time to make the analysis more accurate and here is a link showing video of testing of Apollo space capsule at different entry velocity and angles : https://lnkd.in/drzdU8rf #ANSYS #FEA #SPACECRAFT #SPLASHDWON #ANALSYS #IMPACT #SPACE #APOLLO