Spacecraft Deployables-UMD

8/12/2019 Spacecraft Deployables-UMD

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Space DeployablesPrinciples of Space Systems Design

U N I V E R S I T Y O F

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Applications

solar arrays sun shades solar sails antennas reflective concentrators (mesh and solid) radars

optical metering structures (telescopes,interferometers), full and sparse apertures boom instruments: magnetometers, e-field

measurements orbital dynamics (gravity gradient) momentum transfer (yo-yo despin , 2-point

tethers) large assemblies (space stations , complex

observatories)


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Methods rigid articulating booms articulating lattice masts coilable lattice masts telescoping booms wire booms (centrifugal stiffening) stacers

foldable trusses pop-up trusses foldable panels inflatable structures foam structures free-flying formations 2-point tethered objects (orbit transfer,

electricity generation) large rotating tethered formations


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Deployment Devices (page 1)


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RAE RAE used STEM (structural

tubular extendible mast) booms

to create antennas as long as229-m. The spacecrafts spin

stabilization was reduced using

yo-yo despin throw-away masses.

Lunar orbit

1973

Also known as the DeHavilland boom, developed in 1947

Sunlight on one side

created bowing. STEMS

now use perforated holes

to illuminate backside-

inside, which can be

coated black.

Manufacturing capability

limited, needs continuous

processing technologyfor heat treatment, and

perforations and

coatings. Materials

include BeCu and S.Steel.


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SEASAT / RADARSAT

Synthetic Aperture Radar on anextendible support structure

1mm flatness over 15m length

RADARSAT 1995


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Jumpseat, Trumpet large collectors

Wrap-rib unfurling parabolic

mesh collector, 20 50 meters indiameter. Placed in 12hrMolniya orbits. The wrap-ribdesign has structural ribswrapped around a central hub,then it unwraps at deployment. Iimagine this is a very expensiveway to do this.

SIGINT spy satellites from the

1970s, Trumpets replaced them

in the 1990s


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TDRS solar array, antenna

Older series TDRS. Single Access

antennas on the TDRS. The Harrisdeployable mesh antennas are 4.9

meters (16ft) in diameter.

Similar antenna was used on

GALILEO (it failed to open

properly) The solar arrays used a kapton

facesheet , with holes cut out in

the back facesheet over each

honeycomb cell for radiative

cooling. Newer series TDRS using the taco shellcomposite antenna

TDRS-A 1983

Manufacturing limitations for thin

composite shells are the thermal

gradients developed in the tooling

during curing; this warps the shape into

a potato chip.


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SRTM

At 200 feet, the SRTM ADAM

Mast is the longest man-madehardware to ever fly in space. In

comparison, the Russian Space

Station, Mir, was 108 feet in

length, 98 feet in width, and 89

feet in height. The first U.S.space station, Skylab (1973-74),

with the Apollo Command Module

attached, measured 134 feet in

length by 22 feet in diameter (90

feet with solar arrays open).

2 / 2000

Articulated lattice mast, longest

deployable truss to ever fly. Tip

stable to 10mm


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MilStar

10000 lbs, Titan IV, geostationary

Unfolding truss structure and 16mastromast

1994, 1995,1999

8.5 kw each wing, at 88kg. This worksout to 97 watts per kg, standardtechnology is 30 watts per kg. S/Asimilar to SAFE, ISS


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Wirebooms and stacers

Spinning spacecraft with radialand axial booms

FAST 1996

3m stacer booms

IMAGE 2000

250m long wire booms, !rpm

IMAGE was the longest wire boom to fly, "km in

diameter. The wires were let out very slowly instages. When short, the dog wags the tail, but asit gets longer, the tail starts to wag the dog. Itsas if the wires are springs reaching out frominfinity, giving the core s/c washing-machine cyclemodes. One wire broke after ~4 months in orbit,

due to debris impact.


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TSS-1R

The tether reel mechanism controls

the length, speed, and tension of thetether. The tether reel carries 22 km

(~14 miles) of conducting tether. When

the satellite is fully deployed, and the

tether conductor is pulsed by electron

accelerators, the TSS will be thelongest and lowest frequency antenna

ever placed in orbit. The tether broke

at 20 km during the mission in 1996.

There maybe ~ 100m2of exposed

tether, so the probability of debrisimpact is high.

Think of it as 20km of single point

failures Tether mission deployed from the topof an ABLE fastmast


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Early inflatables The Echo 2 spacecraft was a 41-m

balloon of aluminum foil-mylar

laminate. Echo 2 was designed as a

rigidized passive communications

spacecraft for testing propagation,

tracking, and communication

techniques.

1964 1969Rigidization techniques today:

Stretched aluminum foil, passes yield

and removes wrinkles

Glass transition going cold for

neoprene coated KevlarWater evaporation (corn-starch)

Heat curing pre-preg gr/epoxy

Glass transition for cured epoxy

Inflated to milli-psig. The aluminum foil is rigidized when all the

wrinkles are stretched out, just past the yield point. One blew-up in the

high-bay, knocked the pictures off the wall. Inflation techniques are

compressed gas, and blowing agents as in an automobile airbag.


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Recent inflatables Inflatable Antenna Experiment

The Spartan spacecraft was

rectangular in shape before theantenna inflation. The IAEoccupied about half the volume andthe support systems occupying therest. The IAE is an inflatableantenna 50 feet (14 meters) in

diameter mounted on three 92-foot (28 meter) struts.

1996

The lenticularantenna did not

inflate. Residual

gas partially

popped it out of

the box before it

could be kicked

out to impart

deployment

momentum.


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Thuraya, INMARSAT-4 12-meter TRW AstroMesh reflector

deployed in a manufacturing high bay.

The reflector is one of the largestdeveloped for satellite communications

applications. When stowed, the

reflector folds into a compact package

only 10 percent of its full diameter.

Thuraya 2000

INMARSAT-4 future

Geo-tensoid antenna, but low

frequency of single boom

attachment is a problem.


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Mars Surveyor 2001 Lander

Lander mysteriously canceled UltraFlex is a fan-folded flexible

solar array that deploys to form atensioned ten-sided polygon.Photovoltaic cells are bondeddirectly to the flexible substrate,minimizing complexity and mass.The Mars Surveyor 2001 wings,

each with a diameter of 2 meters,can deploy in a 1 g field andproduce in excess of 105 watts perkilogram.


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NGST deployable optics, deployable sun

6.25m passively-cooled optics, re-scoped from 8m.Tennis-court sized sun shield

TRW / Ball version

Lockheed-Martin version

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Spacecraft Deployables-UMD