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KENNEDY SPACE CENTER, FLA. In the Payload Hazardous Servicing Facility, workers lower the backshell with the Mars Exploration Rover 1 (MER-1) onto the heat shield. The two components form the aeroshell that will protect the rover on its journey to Mars. NASA's twin Mars Exploration Rovers are designed to study the history of water on Mars. These robotic geologists are equipped with a robotic arm, a drilling tool, three spectrometers, and four pairs of cameras that allow them to have a human-like, 3D view of the terrain. Each rover could travel as far as 100 meters in one day to act as Mars scientists' eyes and hands, exploring an environment where humans can't yet go. MER-1 is scheduled to launch June 25 as MER-B aboard a Delta II rocket from Cape Canaveral Air Force Station. Image from NASA, originally appeared on this site: science.ksc.nasa.gov/gallery/photos/ Reposted by San Diego Air and Space Museum
YOKOTA AIR BASE, Japan (Oct. 8, 2013) - From left to right) Airman 1st Class Andrew Fox and Tech. Sgt. Todd Bergin, loadmasters assigned to the 36th Airlift Squadron, deploy a low-cost, low-altitude payload during a Readiness Week training mission. Readiness Week focuses on Yokota's professional airlift mission and developing Airmen's ability to support any contingency in the Pacific. (U.S. Air Force photo by Osakabe Yasuo)
131008-F-PM645-115
** Interested in following U.S. Pacific Command? Engage and connect with us at www.facebook.com/pacific.command and twitter.com/PacificCommand and www.pacom.mil/
Grant Garrity and Max Wasserman take on the challenge of improving the Quest for Stars Payload Design
STS-95 Payload Specialist John H. Glenn Jr., senator from Ohio, reaches to embrace his wife, Annie, after landing at Kennedy Space Center's Shuttle Landing Facility aboard a T-38 jet. Behind the couple is the mate/demate device used to raise and lower the orbiter from its shuttle carrier aircraft during ferry operations. Glenn and other crewmembers flew into KSC to make final preparations for launch. Targeted for liftoff at 2 p.m. on Oct. 29, the STS-95 mission includes research payloads such as the Spartan solar-observing deployable spacecraft, the Hubble Space Telescope Orbital Systems Test Platform, the International Extreme Ultraviolet Hitchhiker, as well as the SPACEHAB single module with experiments on space flight and the aging process. The mission is expected to last 8 days, 21 hours and 49 minutes, and return to KSC on Nov. 7. The other STS-95 crew members are Mission Commander Curtis L. Brown Jr., Pilot Steven W. Lindsey, Mission Specialist Scott E. Parazynski, Mission Specialist Stephen K. Robinson, Mission Specialist Pedro Duque, with the European Space Agency (ESA), and Payload Specialist Chiaki Mukai, with the National Space Development Agency of Japan (NASDA). Image from NASA, originally appeared on this site: science.ksc.nasa.gov/gallery/photos/ Reposted by San Diego Air and Space Museum
16th May 2011
sequence of seven images beginning at T+04 seconds
total sequence time: 7 seconds
viewed large, you can see in the last shot that Endeavour has begun its roll
Payload was the $2billion Alpha Magnetic Spectrometer
A portion of Endeavour's Avionics Bay. The space shuttle avionics system controls assists in controlling most of the shuttle systems. Its functions include automatic determination of the vehicle's status and operational readiness; implementation sequencing and control for the SRB's and ET during launch and ascent; performance monitoring; digital data processing; communications and tracking; payload and system management; guidance, navigation and control; and electrical power distribution for the orbiter, external tank and solid rocket boosters.
The avionics equipment is arranged to facilitate checkout, access and replacement with minimal disturbance to other systems. Almost all electrical and electronic equipment is installed in three areas of the orbiter: the flight deck, the 3 avionics equipment bays in the middeck of the orbiter crew compartment and the three avionics equipment bays in the orbiter aft fuselage. The flight deck of the orbiter crew compartment is the center of avionics activity, both in flight and on the ground. Before launch, the orbiter avionics system is linked to ground support equipment through umbilical connections.
The space shuttle avionics system consists of more than 300 major electronic black boxes located throughout the vehicle, connected by more than 300 miles of electrical wiring. There are approximately 120,400 wire segments and 6,491 connectors in the vehicle. The wiring and connectors weigh approximately 7,000 pounds, wiring alone weighing approximately 4,600 pounds. Total weight of the black boxes, wiring and connectors is approximately 17,116 pounds.
The black boxes are connected to a set of five general-purpose computers through common party lines called data buses. The black boxes offer dual or triple redundancy for every function.
The avionics are designed to withstand multiple failures through redundant hardware and software (computer programs) managed by the complex of five computers; this arrangement is called a fail-operational/fail-safe capability. Fail-operational performance means that, after one failure in a system, redundancy management allows the vehicle to continue on its mission. Fail-safe means that after a second failure, the vehicle still is capable of returning to a landing site safely.
Here are the parts for the OPP MPC Zenith 2 Payloader. You will need a knife and ruler to cut out the fins these aren't the laser cut fins like today's kits. The shock cord in this kit is made of string also the wadding in this kit is like a Brillo pad. The old engines used in this kit were
1st Stage B3-0,B6-0,C6-0.
Upper stage A3-2,B3-3,B6-4,C6-6.
PictionID:53764894 - Catalog:14_032189 - Title:GD/Astronautics Details: Nose Cone Fairing Date: 06/09/1972 - Filename:14_032189.tif - Images from the Convair/General Dynamics Astronautics Atlas Negative Collection. The processing, cataloging and digitization of these images has been made possible by a generous National Historical Publications and Records grant from the National Archives and Records Administration---Please Tag these images so that the information can be permanently stored with the digital file.---Repository: San Diego Air and Space Museum
In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, technicians make preparations to enclose NASA's Mars Science Laboratory (MSL) in an Atlas V rocket payload fairing. The fairing is designed to protect the payload by dampening the sound created by the rocket during liftoff and guard the spacecraft from the impact of aerodynamic pressure and heating during ascent.
MSL's components include a compact car-sized rover, Curiosity, which has 10 science instruments.
Oct. 25, 2011
Under the watchful gaze of payload workers in Hangar AE, Cape Canaveral Air Station, the Wake Shield Facility (WSF) free-flying experiment platform is lowered onto a Shuttle payload bay carrier supporting a containment vessel to protect experiment equipment from contamination prior to deployment during the STS-69 Space Shuttle mission. The disk-shaped satellite is primarily designed to generate an "ultra-vacuum" environment in which to grow and process thin films for next-generation advanced electronics. The ram side of the disk, facing up, houses the avionics platform and other cooperative experiments and space technology applications. Up to seven advanced semiconductor thin films will be grown during the mission on the other side of the disk called the wake side. STS-69 is targeted for a July 20 liftoff aboard Endeavour.
Image from NASA, originally appeared on this site: science.ksc.nasa.gov/gallery/photos/
Reposted by San Diego Air and Space Museum
Presentations on the ExoMars payload by Daniil Rodionov (ACS, FREND) IKI Moscow, Manish Patel (NOMAD) Uni Padua, and Gabriele Cremonese, Co-PI for CASSIS, Astronomical Observatory, Padua. Images credit: ESA/R. Palmari
This is a 1:16 scale model of HX3 Tactical Truck. The model features a 4-axles chassis, up-armored cab, automated load handling system and a replica of 20ft shipping container. Modular design of this model allows to replace the cab as well as a payload in order to demonstrate more options and capabilities.
The model was developed in 3D software. The parts were produced by rapid prototyping from increased durability plastic, manually assembled and painted.
The model is mounted on painted base with acrylic clear protective cover and packed in heavy duty military grade Rotomold transit case.
It was first exhibited at 2022 AUSA trade show where it earned positive feedback for its accuracy, level of detailing and realism.
PictionID:53757960 - Catalog:14_031652 - Title:Atlas 5001 Details: O.A.O. Nose Fairing; Crating for Shipment Date: 05/25/1965 - Filename:14_031652.tif - Images from the Convair/General Dynamics Astronautics Atlas Negative Collection. The processing, cataloging and digitization of these images has been made possible by a generous National Historical Publications and Records grant from the National Archives and Records Administration---Please Tag these images so that the information can be permanently stored with the digital file.---Repository: San Diego Air and Space Museum
NASA’s Pegasus barge arrives at the Launch Complex 39 turn basin at the agency’s Kennedy Space Center in Florida carrying NASA’s Nancy Grace Roman Space Telescope on Sunday, June 21, 2026. Teams will offload and transport the observatory to the spaceport’s Payload Hazardous Servicing Facility where it will undergo processing ahead of launch, targeted no earlier than Sunday, Aug. 30, 2026. Named for NASA’s first chief astronomer and “mother of the Hubble Space Telescope,” Roman will offer a field of view over 100 times larger than Hubble’s to study up to a billion galaxies, directly image exoplanets and planet‑forming disks, and address fundamental questions about dark energy, exoplanets, and infrared astrophysics. Photo credit: NASA/Amber Jean Notvest
NASA image use policy.
The Air Force's Orbital Test Vehicle (OTV) mission, encapsulated inside a 5-meter payload fairing, is mated to its United Launch Alliance (ULA) Atlas V booster inside the Mobile Service Tower at Cape Canaveral's Space Launch Complex-41. Photo credit: United Launch Alliance
Placing the Earth-observer Sentinel-1C onto its "vampire" payload launch adapter to connect the satellite to the Vega-C rocket that will launch it into a polar orbit, 19 November 2024 at Europe Spaceport's payload integration facility.
Earth-observer Sentinel-1C is set to launch on Vega-C rocket flight VV25. At 35 m tall, Vega-C weighs 210 tonnes on the launch pad and reaches orbit with three solid-propellant-powered stages before the fourth liquid-propellant stage takes over for precise placement of Sentinel-1C into its orbit.
The payload adapter connects the satellite and the rocket launching it. The VAMPIRE backronym stands for Vega Adapter for Multiple Payload Injection and Release.
Visible to the right is a fairing half that will protect Sentinel-1C from the elements on the launch pad and during launch through our atmosphere.
Carrying advanced radar technology to provide an all-weather, day-and-night supply of imagery of Earth’s surface, the ambitious Copernicus Sentinel-1 mission has raised the bar for spaceborne radar.
The mission benefits numerous Copernicus services and applications such as those that relate to Arctic sea-ice monitoring, iceberg tracking, routine sea-ice mapping, glacier-velocity monitoring, surveillance of the marine environment including oil-spill monitoring and ship detection for maritime security as well as illegal fisheries monitoring.
Europe’s Vega-C rocket can launch 2300 kg into space, such as small scientific and Earth observation spacecraft. Vega-C is the evolution of the Vega family of rockets and delivers increased performance, greater payload volume and improved competitiveness.
Credits: ESA/CNES/Arianespace/Optique du vidéo du CSG–S. Martin
the Plympton-Wyoming Caterpillar 928G Payloader was employed for 6 hours clearing this section of road from a substantial drift after a 3 day blizzard. The snow in that spot was just too deep for the regular plows. (Plympton-Wyoming, Lambton County, Ontario)
JSC2001-02471 (18 September 2001) --- Payload specialist Ilan Ramon (left), astronauts Laurel B. Clark, mission specialist, and Michael P. Anderson, payload commander, participate in mission training in one of the high fidelity trainers/mockups in the Space Vehicle Mockup Facility at the Johnson Space Center (JSC). The three, attired in training versions of the full-pressure launch and entry suit, are seated on the mid deck for an emergency egress training session. Ramon represents the Israeli Space Agency.
Grey Eagle - Hypersonic Bomber Mach 8 - 10, IO Aircraft www.ioaircraft.com
Length: 150'
Span: 71'
Engines: 4 U-TBCC (Unified Turbine Based Combined Cycle)
1 Air Breathing Aerospike
Fuel: Kero / Hydrogen
Payload: Up 36 2,000 LBS JDAM's, or 80,000 LBS
Range: 10,000nm + Aerial Refueling Capable
www.ioaircraft.com/hypersonic.php
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Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
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Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
PictionID:44810029 - Catalog:14_014314 - Title:Atlas Payload Component - Filename:14_014314.TIF - - - Image from the Convair/General Dynamics Astronautics Atlas Negative Collection. The processing, cataloging and digitization of these images has been made possible by a generous National Historical Publications and Records grant from the National Archives and Records Administration---Please Tag these images so that the information can be permanently stored with the digital file.---Repository: San Diego Air and Space Museum
STS-85 Payload Commander N. Jan Davis gives a thumb-up as she is assisted with her ascent/reentry flight suit in the Operations and Checkout (O&C) Building. She has logged nearly 400 hours in space on the STS-47 and STS-60 missions and holds a doctorate in mechanical engineering. Davis will have overall responsibility for the experiments conducted on STS-85. She will also deploy and retrieve the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere- Shuttle Pallet Satellite-2 (CRISTA-SPAS-2) free- flyer and operate the prototype Japanese robotic arm. The primary payload aboard the Space Shuttle orbiter Discovery is the CRISTA- SPAS-2. Other payloads on the 11-day mission include the Manipulator Flight Demonstration (MFD), and Technology Applications and Science-1 (TAS-1) and International Extreme Ultraviolet Hitchhiker-2 (IEH-2) experiments. Image from NASA, originally appeared on this site: science.ksc.nasa.gov/gallery/photos/ Reposted by San Diego Air and Space Museum
Dassault/Dornier Alpha Jet showing its payload. Seen at the Frankfurt Airshow in 1976 with the ill fated VFW 614 behind it.
Old slide scan
United Launch Alliance (ULA) hoists the USSF-87 mission payload atop the Vulcan rocket in the Government Vertical Integration Facility (VIF-G) adjacent to Space Launch Complex-41 at Cape Canaveral Space Force Station. This will be Vulcan's second national security mission for the U.S. Space Force's Space Systems Command (SSC). Photo credit: United Launch Alliance
United Launch Alliance (ULA) hoists the USSF-87 mission payload atop the Vulcan rocket in the Government Vertical Integration Facility (VIF-G) adjacent to Space Launch Complex-41 at Cape Canaveral Space Force Station. This will be Vulcan's second national security mission for the U.S. Space Force's Space Systems Command (SSC). Photo credit: United Launch Alliance
Shuttle Radar Topography Mission Payload
In 2000, Space Shuttle Endeavour carried into orbit the Shuttle Radar Topography Mission (SRTM) payload, a novel system used to produce a highly detailed three-dimensional map of more than 70 percent of the Earth’s surface. The mast canister and outboard structure and antennas displayed here were crucial components of that payload.
SRTM featured a main antenna in the Shuttle payload bay, a folding mast 60 meters (197 feet) long, and another antenna at the end of the mast. This dual antenna system -- the largest rigid structure then flown in space -- produced 3-D mapping through interferometry, a technique for combining data obtained separately by the two antennas. SRTM was a joint undertaking of NASA’s Jet Propulsion Laboratory and the Defense Department’s National Imagery and mapping Agency. The military will use the highest resolution data for terrain navigation for airplanes and cruise missiles. Lower resolution data will be made available to civilian scientists and others.
Mast canister (undeployed)
Length:
2.9 m (9 ft 7 in)
Width:
1.4 m (4ft 5in)
Weight:
985 kg (2,170 lb)
Manufacturer:
AEC-Able Engineering Co.
Outboard support structure and antenna
Length:
8 m (26 ft 4 in)
Width:
2 m (6 ft 6 in)
Height:
.9 m (2 ft)
Weight:
360 kg (794 lb)
Manufacturer:
Ball Telecommunications Products Div. and Composite Optics, Inc.
A shipping container with payload flight hardware for the Third Hubble Space Telescope Servicing Mission (SM-3A) is transferred onto a transporter from the C-5 air cargo plane that brought it to KSC. The hardware will be taken to the Payload Hazardous Servicing Facility for final testing and integration of payload elements. Mission STS-103 is a "call-up" mission which is being planned due to the need to replace portions of the Hubble's pointing system, the gyros, which have begun to fail. Although Hubble is operating normally and conducting its scientific observations, only three of its six gyroscopes are working properly. The gyroscopes allow the telescope to point at stars, galaxies and planets. The STS-103 crew will not only replace gyroscopes, it will also replace a Fine Guidance Sensor and an older computer with a new enhanced model, an older data tape recorder with a solid state digital recorder, a failed spare transmitter with a new one, and degraded insulation on the telescope with new thermal insulation. The crew will also install a Battery Voltage/Temperature Improvement Kit to protect the spacecraft batteries from overcharging and overheating when the telescope goes into a safe mode. Launch of STS-93 is currently targeted for Oct. 14 but under review, pending the launch date of a prior mission, STS-99, also under review. Image from NASA, originally appeared on this site: science.ksc.nasa.gov/gallery/photos/ Reposted by San Diego Air and Space Museum
The Lunar Roving Vehicle had a mass of 463 lbs and was designed to hold a payload of an additional 1,080 lbs on the lunar surface. The frame was 10 feet long with a wheelbase of 7.5 feet. The maximum height was 3.75 feet. The frame was made of aluminum alloy 2219 tubing welded assemblies and consisted of a 3 part chassis which was hinged in the center so it could be folded up and hung in the Lunar Module quad 1 bay. It had two side-by-side foldable seats made of tubular aluminum with nylon webbing and aluminum floor panels. An armrest was mounted between the seats, and each seat had adjustable footrests and a velcro seatbelt. A large mesh dish antenna was mounted on a mast on the front center of the rover. The suspension consisted of a double horizontal wishbone with upper and lower torsion bars and a damper unit between the chassis and upper wishbone. Fully loaded the LRV had a ground clearance of 14 inches.
The wheels consisted of a spun aluminum hub and an 32 inches diameter, 9 inch wide tire made of zinc coated woven .033 inch diameter steel strands attached to the rim and discs of formed aluminum. Titanium chevrons covered 50% of the contact area to provide traction. Inside the tire was a 25.5 inch diameter bump stop frame to protect the hub. Dust guards were mounted above the wheels. Each wheel had its own electric drive, a DC series wound 0.25 hp motor capable of 10,000 rpm, attached to the wheel via an 80:1 harmonic drive, and a mechanical brake unit. Maneuvering capability was provided through the use of front and rear steering motors. Each series wound DC steering motor was capable of 0.1 hp. Both sets of wheels would turn in opposite directions, giving a steering radius of 10 feet, or could be decoupled so only one set would be used for steering. They could also free-wheel in case of drive failure. Power was provided by two 36-volt silver-zinc potassium hydroxide non-rechargeable batteries with a capacity of 121 A·h. These were used to power the drive and steering motors and also a 36 volt utility outlet mounted on front of the LRV to power the communications relay unit or the TV camera.
A T-shaped hand controller situated between the two seats controlled the four drive motors, two steering motors and brakes. Moving the stick forward powered the LRV forward, left and right turned the vehicle left or right, pulling backwards activated the brakes. Activating a switch on the handle before pulling back would put the LRV into reverse. Pulling the handle all the way back activated a parking brake. The control and display modules were situated in front of the handle and gave information on the speed, heading, pitch, and power and temperature levels.
Navigation was based on continuously recording direction and distance through use of a directional gyro and odometer and inputting this data to a computer which would keep track of the overall direction and distance back to the LM. There was also a Sun-shadow device which could give a manual heading based on the direction of the Sun, using the fact that the Sun moved very slowly in the sky.
United Launch Alliance (ULA) hoists the Amazon Leo mission payload atop the Atlas V rocket in the Vertical Integration Facility adjacent to Space Launch Complex-41 at Cape Canaveral Space Force Station. The Atlas V will launch the Leo 8 mission for Amazon's broadband satellite constellation. Photo credit: United Launch Alliance
A photograph shows the exterior of NASA’s Payload Hazardous Servicing Facility (PHSF) on Tuesday, April 21, 2026, at NASA’s Kennedy Space Center in Florida. Recently, technicians performed several upgrades to the facility ahead of the arrival of the agency’s Nancy Grace Roman Space Telescope, designed to provide deep, panoramic views of the cosmos, generating never-before-seen pictures that will revolutionize our understanding of the universe. Roman will undergo several prelaunch operations, including thermal protection closeout, cleaning, solar array work, and loading hydrazine propellant. The PHSF is one of the very few facilities where spacecraft undergo both hazardous fueling operations and delicate contamination control procedures. Photo credit: NASA/Kim Shiflett
NASA image use policy.
NASA's Wallops Flight Facility C-130 aircraft delivered the agency’s Galactic/Extragalactic ULDB Spectroscopic Terahertz Observatory (GUSTO) payload to McMurdo Station, Antarctica, on Oct. 28, 2023. The GUSTO mission will launch on a scientific balloon in December 2023.
NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission.
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One last shot of her abdomen with missile ports open. The missile payload (not counting internal magazines) goes:
80 Short Range Missiles (legs)
28 Anti Air Missiles (tail end)
30 Medium Range Missiles (back end)
16 Long Range Missiles (sides)
6 ICBMs (top back)
Jet Propulsion Laboratory workers in the Payload Hazardous Servicing Facility (PHSF) are repairing two cracked solar cells on the Mars Global Surveyor solar panels. The panels, extending from the bus of the spacecraft, are partly covered with a protective cloth. The Global Surveyor features four solar array panels as part of its electrical power subsystem; the panels will provide electricity to operate the spacecraft and its scientific instruments. Two nickel hydrogen batteries will do the job when the arrays are not illuminated. The Mars Global Surveyor is on track for a launch Nov. 6 at the beginning of a 20-day launch period aboard a Delta II expendable launch vehicle.
PictionID:53766890 - Catalog:14_031645 - Title:Atlas Centaur 6 Details: AC-6 Nose Fairing Package Date: 05/22/1965 - Filename:14_031645.TIF - Images from the Convair/General Dynamics Astronautics Atlas Negative Collection. The processing, cataloging and digitization of these images has been made possible by a generous National Historical Publications and Records grant from the National Archives and Records Administration---Please Tag these images so that the information can be permanently stored with the digital file.---Repository: San Diego Air and Space Museum
The National Reconnaissance Office’s NROL-38 satellite, encapsulated inside a 4-meter payload fairing, is mated to its United Launch Alliance Atlas V booster at Cape Canaveral's Space Launch Complex-41. Photo credit: United Launch Alliance
United Launch Alliance (ULA) hoists the Kuiper 2 mission payload atop the Atlas V rocket in the Vertical Integration Facility adjacent to Space Launch Complex-41 at Cape Canaveral Space Force Station. The Atlas V will launch the Leo 4 mission for Amazon's broadband satellite constellation. Photo credit: United Launch Alliance
The National Reconnaissance Office’s NROL-38 satellite, encapsulated inside a 4-meter payload fairing, is mated to its United Launch Alliance Atlas V booster at Cape Canaveral's Space Launch Complex-41. Photo credit: United Launch Alliance
KENNEDY SPACE CENTER, FLA. In the Payload Hazardous Servicing Facility, an electromagnetic interference verification test is being conducted on the solar arrays for the Mars Reconnaissance Orbiter (MRO) and an antenna simulator (yellow horizontal rod). If no interference is found during the test, the Shallow Radar Antenna (SHARAD) will be installed on the spacecraft. The spacecraft is undergoing multiple mechanical assembly operations and electrical tests to verify its readiness for launch. The MRO was built by Lockheed Martin for NASAs Jet Propulsion Laboratory in California. It is the next major step in Mars exploration and scheduled for launch from Launch Complex 41 at Cape Canaveral Air Force Station in a window opening Aug. 10. The MRO is an important next step in fulfilling NASAs vision of space exploration and ultimately sending human explorers to Mars and beyond. Image from NASA, originally appeared on this site: science.ksc.nasa.gov/gallery/photos/ Reposted by San Diego Air and Space Museum
KENNEDY SPACE CENTER, FLA. In the Payload Hazardous Servicing Facility, workers from Lockheed Martin prepare to deploy the solar array on the Mars Reconnaissance Orbiter (MRO). After solar array testing, the MRO will be transported to the Vertical Installation Facility in late July. It will join the Atlas V for the final phase of launch preparations. The spacecraft is then scheduled to undergo a functional test, and a final week of integrated testing and closeouts. The MRO was built by Lockheed Martin for the Jet Propulsion Laboratory in California. It is the next major step in Mars exploration and scheduled for launch from Cape Canaveral Air Force Station in a window opening Aug. 10. The MRO is an important next step in fulfilling NASAs vision of space exploration and ultimately sending human explorers to Mars and beyond. Image from NASA, originally appeared on this site: science.ksc.nasa.gov/gallery/photos/ Reposted by San Diego Air and Space Museum
This photograph was published in an online magazine article in DEVON LIVE, on 10th December 2024, written by Victoria Chessum & Lauren Haughey (Lifestyle and Money Reporter), titled:
'' Warning to place bird feeders 'the right way' to avoid garden pests -
Gardeners' World has urged green-thumbed fans to carefully consider the placement of bird feeders in their gardens ''.
Devon Live has offices in South Devon, North Devon and Exeter and community correspondents and columnists around the county. Articles are in print in the Express & Echo, the Torquay Herald Express, the Mid Devon Gazette and the North Devon Journal.
They are part of Reach Plc, which is a member of and regulated by IPSO, the Independent Press Standards Organisation.
This photograph had previously been Selected for sale in the GETTY IMAGES COLLECTION on September 9th 2020
CREATIVE RF gty.im/1271274444 MOMENT ROYALTY FREE COLLECTION and became my 4,588th frame for sale in the Getty Images collection, I now have 7,000+ images and Getty are my sole worldwide agent.
©All photographs on this site are copyright: ©DESPITE STRAIGHT LINES (Paul Williams) 2011 – 2021 & GETTY IMAGES ®
No license is given nor granted in respect of the use of any copyrighted material on this site other than with the express written agreement of ©DESPITE STRAIGHT LINES (Paul Williams). No image may be used as source material for paintings, drawings, sculptures, or any other art form without permission and/or compensation to ©DESPITE STRAIGHT LINES (Paul Williams)
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Photograph taken at an altitude of Fifty one metres at 10:38am on Monday 7th September 2020, of a male Blue Tit (Parus caeruleus), after a summer rain shower off Chessington Avenue in Bexleyheath, Kent.
The male is identified by a more striking blue skull cap,darker blacker around the eyes and around the chin, a darker taile and more vibrant plumage than the female and these little birds are bestowed with wonderful acrobatic skills.
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Nikon D850 Focal length 600mm Shutter speed: 1/200s Aperture f/6.3 iso200 Image area FX (36 x 24) NEF RAW L (8256 x 5504). NEF RAW L (14 bit uncompressed) Image size L (8256 x 5504 FX). Focus mode AF-C focus. AF-C Priority Selection: Release. Nikon Back button focusing enabled. AF-S Priority selection: Focus. 3D Tracking watch area: Normal 55 Tracking points.AF-Area mode single point & 73 point switchable. Exposure mode: Shutter Priority mode. Matrix metering. Auto ISO sensitivity control on (Max iso 800/ Minimum shutter speed 125). White balance on: Auto1. Colour space: RGB. Active D-lighting: Normal. Vignette control: Normal. Nikon Distortion control: Enabled. Picture control: Auto (Sharpening A +1/Clarity A+1)
Sigma 60-600mm f/4.5-6.3DG OS HSM SPORTS. Lee SW150 MKI filter holder with MK2 light shield and custom made velcro fitting for the Sigma lens. Lee SW150 circular polariser glass filter.Lee SW150 Filters field pouch.Nikon GP-1 GPS module. Hoodman HEYENRG round eyepiece oversized eyecup.Manfrotto MT057C3-G Carbon fibre geared tripod. Neewer Gimbal tripod head with Arca Swiss quick release plate.055XPROB Tripod 3 Sections (Payload: 5.6kgs). Mcoplus professional MB-D850 multi function battery grip 6960.Two Nikon EN-EL15a batteries (Priority to battery in Battery grip). Matin quick release neckstrap. My Memory 128GB Class 10 SDXC 80MB/s card. Lowepro Flipside 400 AW camera bag.
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LATITUDE: N 51d 28m 27.97s
LONGITUDE: E 0d 8m 10.29s
ALTITUDE: 51.0m
RAW (TIFF) FILE: 130.00MB NEF: 91.8MB
PROCESSED (JPeg) FILE: 24.70MB
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PROCESSING POWER:
Nikon D850 Firmware versions C 1.10 (9/05/2019) LD Distortion Data 2.018 (18/02/20) LF 1.00
HP 110-352na Desktop PC with AMD Quad-Core A6-5200 APU 64Bit processor. Radeon HD8400 graphics. 8 GB DDR3 Memory with 1TB Data storage. 64-bit Windows 10. Verbatim USB 2.0 1TB desktop hard drive. WD My Passport Ultra 1tb USB3 Portable hard drive. Nikon ViewNX-1 64bit Version 1.4.1 (18/02/2020). Nikon Capture NX-D 64bit Version 1.6.2 (18/02/2020). Nikon Picture Control Utility 2 (Version 2.4.5 (18/02/2020). Nikon Transfer 2 Version 2.13.5. Adobe photoshop Elements 8 Version 8.0 64bit.
United Launch Alliance (ULA) hoists the Kuiper 2 mission payload atop the Atlas V rocket in the Vertical Integration Facility adjacent to Space Launch Complex-41 at Cape Canaveral Space Force Station. The Atlas V will launch the Leo 4 mission for Amazon's broadband satellite constellation. Photo credit: United Launch Alliance
PictionID:55778994 - Catalog:GD/Astronautics Testing Details: Nose Cone Fairing; Jettison Test Date: 08/09/1961 - Title:Array - Filename:14_037952.tif - ---- Images from the Convair/General Dynamics Astronautics Atlas Negative Collection. The processing, cataloging and digitization of these images has been made possible by a generous National Historical Publications and Records grant from the National Archives and Records Administration---Please Tag these images so that the information can be permanently stored with the digital file.---Repository: San Diego Air and Space Museum
Inside the Payload Changeout Room (PCR) in the Rotating Service Structure (RSS) at Launch Pad 39-B, technicians in clean suits move the payloads for mission STS-95 to the payload bay of Space Shuttle Discovery. At the top of the RSS is the Spacehab module; below it are the Spartan solar-observing deployable spacecraft, the Hubble Space Telescope Orbiting Systems Test Platform (HOST), and the International Extreme Ultraviolet Hitchhiker (IEH-3). The PCR is an environmentally controlled facility with seals around the mating surface that fit against the orbiter or payload canister and permit the payload bay or canister doors to be opened and cargo removed without exposing it to outside air and contaminants. Payloads are installed vertically in the orbiter using the extendable payload ground handling mechanism. Fixed and extendable work platforms provide work access in the PCR. The SPACEHAB single module involves experiments on space flight and the aging process. Spartan is a solar physics spacecraft designed to perform remote sensing of the hot outer layers of the sun's atmosphere or corona. HOST carries four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an Earth-orbiting environment. IEH-3 comprises several experiments that will study the Jovian planetary system, hot stars, planetary and reflection nebulae, other stellar objects and their environments through remote observation of EUV/FUV emissions; study spacecraft interactions, Shuttle glow, thruster firings, and contamination; and measure the solar constant and identify variations in the value during a solar cycle. Mission STS-95 is scheduled to launch Oct. 29, 1998. Image from NASA, originally appeared on this site: science.ksc.nasa.gov/gallery/photos/ Reposted by San Diego Air and Space Museum
The National Reconnaissance Office’s NROL-25 satellite, encapsulated inside a 4-meter payload fairing, is mated to its United Launch Alliance (ULA) Delta IV booster inside the Mobile Service Tower (MST) at Space Launch Complex-6 at Vandenberg Air Force Base, California. Photo credit: United Launch Alliance