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From Space.com's NASA's Piggyback Experiment on Israeli Moon Lander Could Aid Future Lunar Touchdowns shows an image of the laser altimeter on the LRO. It looks like the "transmit" and "receive" telescopes are both based on lenses rather than mirrors.

I think that this is pretty atypical for space-based telescopes.

  • Why were lenses used in this case?
  • Were there advantages over mirrors?
  • Where there any recognized disadvantages? Mechanical or optical?

THere's more about LOLA here: https://lola.gsfc.nasa.gov/images/smith_lola_ssr09.pdf


The Lunar Orbiter Laser Altimeter (LOLA) instrument, which is carried aboard NASA's Lunar Reconnaissance Orbiter. LOLA will laser-range a retro-reflector array mounted atop Israel's Beresheet moon lander. Image: NASA

enter image description here

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  • $\begingroup$ At the inexpensive terrestrial hobbyist optical telescope level, refractor scopes (lenses) tend to be more robust. Reflector scopes (mirrors) offer bigger apertures to collect more light, at the cost of being delicate and prone to going out of alignment. $\endgroup$ – Russell Borogove Jun 1 at 13:21
  • $\begingroup$ Considering that it is monochromatic (laser) and that it is being used for ranging (rather than imaging), perhaps the usual drawbacks of lenses may not be an issue. $\endgroup$ – DrSheldon Jun 1 at 14:42
  • $\begingroup$ @DrSheldon What's the thickness and weight of that short focal length, large diameter lens shown in the picture $\endgroup$ – uhoh Jun 1 at 16:51
  • $\begingroup$ @RussellBorogove In space, to my knowledge, both large and small diameter telescopes are almost exclusively reflecting. I've never seen anything like this before! That's 1 inch or 25 mm hole spacing on the optical table, this looks like it could be an 8 inch diameter lens or larger. With such a short focal length, it must be very thick and very heavy compared to a silicon carbide mirror. The only time I've seen lenses used for anything except star cameras is when they are necessary; compound lenses for fields wider than you can easily do with mirrors. $\endgroup$ – uhoh Jun 1 at 17:00
  • $\begingroup$ @uhoh Most space telescopes aren't looking for light emitted only 3600km away. $\endgroup$ – Russell Borogove Jun 1 at 17:12
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tl;dr: The 125 mm proven receiving telescope design used on the receiving telescope of the MLA laser ranger used on MESSENGER was adapted and enlarged to 150 mm for the LOLA of LRO. I am guessing that this was felt far more prudent than a new design using reflective optics based on exotic materials like silicon carbide.


This page on LOLA links to

and that paper references the Mercury Laser Altimeter or MLA:

See also

The earlier Mercury Laser altimeter

...was used on the 2004 MESSENGER mission to Mercury. The design was developed to handle large thermal swings and also large thermal gradients within the spacecraft and within the telescope itself.

It used four telescopes in parallel, each with 125 mm (five inch) objective lenses to collect the weak scattered photons from the planets surface and image them on to silicon avalanche photodiodes (SiAPDs) for timing analysis.

  1. Receiver Telescope

The four MLA Receiver Telescopes have a combined aperture of 417 cm2 and a 400rad-diameter nominal FOV. The collecting area is equivalent to a single 0.25m-diameter telescope with a 15% secondary and spider obscuration factor. The original MLA receiver concept was based on a scaled-down version of the beryllium Cassegrain telescopes used on MOLA (0.5 m in diameter) and GLAS (1.0 m in diameter), but once the MESSENGER thermal environment was better understood it became apparent that this telescope would not meet the MLA on-orbit performance requirements. Although the MOLA and GLAS telescopes are athermal (to first order) under a bulk temperature change, they are very sensitive to axial and radial thermal gradients because of the high coefficient of thermal expansion (CTE) of beryllium and the large longitudinal magnification and fast primary of the Cassegrain telescope design.8 The multiaperture, refractive MLA Receiver Telescope design is not athermal, but this optical design can handle thermal gradients an order of magnitude larger than an equivalent beryllium Cassegrain telescope for a comparable amount of image degradation. The MLA Receiver Telescope operating thermal range is 20 25ºC, and the survival thermal range is 30 to 60 ºC. The optical layout of the MLA Receiver Telescope is in Fig. 3. The telescope is a four-element reverse telephoto design with a 500mm focal length, a 300mm unfolded path length, and a final speed of f4.35. The plano–convex objective lens is made of sapphire and has a focal length of 311.2 mm, a diameter of 125 mm, and a mounted clear aperture diameter of 115 mm. Sapphire was selected for all the optics exposed to the Mercury environment for its ability to withstand thermal shocks,9 its lower absorption in the IR compared with optical glasses, and its resistance to radiation darkening. Although sapphire is birefringent and can generate double images, its imaging performance is adequate for the MLA receiver photon bucket. Ten high-purity, synthetic sapphire blanks are manufactured by Crystal Systems, and the blanks are ground and polished into lenses by Meller Optics. A negative focal-length triplet lens group increases the focal length of the objective lens and corrects spherical aberration and coma. The triplet is manufactured out of radiation-resistant Schott BK7G18 glass by Optimax Systems. The telescope is folded to fit within the allocated MLA volume, which also helps reduce the cantilevered mass. The dielectric fold mirror reflects only a small spectral band centered at 1064 nm, which provides protection against an accidental view of the Sun since most of the visible solar radiation goes through the fold mirror and scatters off its frosted backside onto the MESSENGER instrument deck.

The system was extensively modeled and tested for the thermal performance. The paper describes this in detail, here is a small sample:

The Receiver Telescope optothermal model accounted for both changes to the objective lens shape and index of refraction and mechanical deformations of the beryllium telescope tube. The thermal analysis was performed by Harvard Thermal Inc. based on the calculated absorbed IR flux from the TracePro Mercury MLA model. The thermal analysis showed that the Receiver Telescope develops the expected 30 ºC axial gradient plus a 10 ºC radial gradient (Fig. 6). The perturbed optical system is then ray traced with OSLO to calculate the effects on image size and location: The image defocused as expected, but the telescope line-of-sight change was only 15 rad, which is small enough to be neglected.

Optical system design and integration of the Mercury Laser Altimeter Optical system design and integration of the Mercury Laser Altimeter


The proven design was adapted for LOLA

I am speculating that rather than develop a reflective optics system based on a new material like silicon carbide for low-thermal-expansion optics and mechanics, the designers opted for a small modification of a proven, well-characterized design.

  1. Lunar Orbiter Laser Altimeter Receiver Telescope

The LOLA Receiver Telescope is a scaled up version of one of the MLA receiver telescopes. Both are 500 mm EFL telephoto designs, but the LOLA telescope has a larger diameter objective lens (150 mm versus 125 mm) and a longer unfolded path length to preserve the f =2 objective lens speed. MLA used a sapphire objective lens for its ability to survive in harsh thermal environments, but sapphire has the drawback of having a high density. To try to reduce mass we also designed, built, and tested an engineering model (EM) LOLA receiver Telescope using a BK7G18 objective lens. The optical layout for both LOLA Receiver Telescope designs is shown in Fig. 5. The BK7G18 design has fewer elements because the objective lens is aspheric, and a single negative lens can set the final telescope EFL without the need to correct for the spherical aberration of the objective lens. The mass savings of this design were significant (220 g), and its defocus versus operating temperature negligible since BK7G18 has a dn/dT an order of magnitude smaller than sapphire, but the LOLA thermal model predicted that the BK7G18 objective lens would operate with large thermal gradients during orbit around the Moon due to the high emissivity and poor thermal conductivity of BK7G18. Figure 6 shows the predicted on-orbit temperatures for the two objective lens materials for the LRO Hot and Cold thermal cases; temperatures at the lens edge and lens internal and external center points are shown over a time period of three orbits. The sapphire objective lens operates over a temperature range of þ11 °C to þ42 °C with negligible thermal gradients, while the BK7G18 objective lens operates over a wider −24 °C to þ56 °C temperature range and with radial and axial thermal gradients of up to 25 °C. The large and constantly changing thermal gradient would bend the BK7G18 objective lens back and forth during each LRO orbit. Although structural analysis and testing of the BK7G18 objective lens indicated that the lens would survive the predicted on-orbit thermal environment, we decided that it was safer to use the MLA heritage telescope design for LOLA.

Optical system design and integration of the Lunar orbiter Laser Altimeter

Optical system design and integration of the Lunar orbiter Laser Altimeter

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