Suborbital Balloot

Watched a bit of the two suborbital flights, not that much though, certainly not with the interest I would have had roughly a decade and a half ago. I had thought back then that the technical route to routine space travel would be through incremental advancements from suborbital to orbital to cislunar to other planets and asteroids. Looks like I was wrong again.

One thing that stood out to me was the people trying to play in microgravity with limited room in which to do it. Much more limited in volume and more clutter than on the ZeroGee flights. Looked to me like time was limited enough that there was just time to glance out the windows and play half a round of ZeeGee catch.

A balloot in the spirit of the inflatable space structures might help here if some problems of fast deployment, rapid access, and safety could be addressed. A 5-10 meter diameter inflatable without seats and other clutter would give considerably more play room than either SS2 or NS. Fast deployment might be a bit of a challenge as there wouldn’t be time for a leisurely five minute deployment and check out.

I don’t see how the idea could be adapted to SS2, but it does seem that a VTVL ship could have a fast clamshell hatch in the nose that could allow people in a fairly tight cabin access to a large play area within seconds of reaching vacuum and engine cut off. So a ship that would have had six people might fly with a dozen, each of which would have a lot more room to play and experiment.

With a large balloot starting deceleration at much higher altitude, it seems possible that a ship could fly much higher without subjecting the participants to excessive gee loads. Every extra Mach number gives on the order of another minute of play time in microgravity. On the way back, the participants get back to their seats while the hatch closes. The balloot remains deployed until landing as a drag device incidentally reducing terminal velocity considerably, possibly enough to make a failure of engine relight survivable, if painful.

This seems to me an idea that, even if feasible, is very late to the party. It looks like orbital tourism is likely to become fully operational in the same timeframe as the two suborbital contenders. The contrast may well cut into the desirability of the short pop ups. One interesting factoid though is that the people that were insisting that orbital was 64 times as hard as suborbital have to be wondering what the two companies could have accomplished with 64 times the investment.

Posted in Uncategorized | 9 Comments

Layover Lunar Lander

A lunar lander concept I haven’t seen elsewhere is a layover concept. A tall ship lands on its’ tail the way the several suborbital hoppers and the Falcon9 has been doing for several years now. After landing and checking the area to one side, a small thruster tips it over on two legs. Before reaching the surface, some landing rockets in the nose fire to bring velocity to zero as the nose lands on a couple more much smaller legs.

If the lander is 100 meters tall, the terminal velocity that must be braked before the nose landing is under 20 m/s. Stopping 100 tons just at the surface would require between 400 and 700 kg of propellant depending on the Isp in use. If feasible, seems like a fair trade off as opposed to raising and lowering people, supplies, and equipment 100 meters for the duration of the mission.

The lower legs on the pivot side would need to be able to handle loads from two directions, though the legs at the nose could be quite light. One alternative leg option is to have the lower pivoting legs articulate up under the body of the vehicle to split the loading better and to reduce braking thrust requirements a bit more.

The tip over landing should be quite simple as there would be no question of where the vehicle is in relation to the ground at any given time. Of course smaller vehicles would have even less trouble and use less propellant. A 20 meter high vehicle with a 10 ton payload would require only 20-30 kg of braking propellant.

Posted in Uncategorized | 24 Comments

Unorthodox Reusable Lunar Landers Concepts

[Author’s Note: Back in summer of 2019, shortly after Mike Pence announced the goal of having NASA return astronauts to the lunar surface for the first time in over half a century, I had the idea of doing a blog post about the benefits of fully-reusable lunar landers, and then going over a few of my favorite unorthodox reusable lunar lander configurations. I got side-tracked at the time by my entrepreneurial day job1, and by the time I freed up from that, Altius was busy supporting one of the three Artemis HLS teams, so I felt a blog post like this might be impolitic. Now that we’re no longer actively supporting that team, and given that I no longer have running a startup as an excuse for not blogging, I wanted to finish fleshing out these ideas and at least get them out there for discussion.]

While traditionally most lunar landers and lander conceptual designs have been fully-expendable, many people, including NASA have begun to see some of the benefits of reusable lunar lander systems. Some of those benefits as I see them include:

  • Lowers the cost of sending hardware to the Moon: This is the obvious one that people get about reusability, is that so long as it’s done right, it can significantly lower the per mission cost, especially if the lander can be reused many times over its lifetime.
  • Makes the program easier to throttle up or down: One of the big challenges the Augustine Commission noticed for NASA Human Spaceflight missions was that they could rarely afford to both develop new capabilities while operating previous ones. With a fully-reusable lander system, especially one designed to not require a huge standing arm to support it, much of the cost of a given mission could be the marginal cost of launching new crew/cargo/propellant, which means it’s easier to throttle down temporarily without losing the capability.
  • More amenable to non-critical-path international participation: With reusable landers, once they’re launched, incremental missions mostly require refueling, reprovisioning, and a crew swapout. Government space agencies typically don’t want to spend money outside of their country–they typically try to find a way where they can handle things through barter and no-exchange-of-funds agreements. For instance, in exchange for getting some of the ISS crew slots, Japan and ESA both developed cargo vehicles to bring some of the cargo that ISS needed. So they could spend their space agency money locally, and use that contribution to get ISS astronaut slots without having to develop their own crew launch capabilities2. Reusable lunar landers provide an easy barter option for international participation in NASA lunar missions — launching propellant and/or cargo. The nice thing is that if done wisely (say using a Low-Orbit HSF Depot in LEO), this might require minimal development cost for foreign countries, while allowing them to usefully contribute, but in a way where they’re not on the critical path, and they can throttle up or down their involvement as desired.
  • Creates near-term demand for lunar ISRU: Once you have reusable lunar landers, the vast majority of the mass needed per mission is propellant. Being able to source that locally could significantly reduce the cost of missions3, and could increase the capability of landers by enabling them to be refueled both in orbit and on the surface4. With reusable landers, you have established demand at an established price point, which makes closing the business case for lunar ISRU easier, so long as you can truly extract it cheaper than shipping it from Earth5.
  • Enables a much more ambitious exploration program: This should be obvious, but once you have reusable landers, you have tons more flexibility for doing things beyond simple flags-and-footprints missions. Things like lunar search and rescue, doing suborbital sorties from a bigger outpost to explore areas of economic or scientific interest, etc. become more feasible.

Anyhow, if you’re reading this blog, I’m probably preaching to the choir here, but I wanted to lay out some of my thoughts on why reusable lunar landers matter.

Unorthodox Reusable Lander Concepts

Given the desirability of fully-reusable lunar landers, it’s sad that most of the best-known reusable lander concepts have used a very similar landing configuration — tall skinny landers with the crew and cargo mounted on top.

Traditional Reusable Lander Concepts: One Long Elevator Ride for a Man, One Griant Crane for Cargo… (credits: SpaceX, Chesley Bonestell x2, Lockheed Martin)

In this series I wanted to highlight a few other potential fully-reusable lander configurations worth considering, some thoughts on variations on the themes, and their pros and cons. Only maybe one of these configurations is one I could claim to have invented, but I thought it would be worth highlighting some other good ideas that may or may not be as well known, especially to younger space engineers or enthusiasts.

In the following parts I’d like to discuss the following reusable lunar lander configurations:

  1. Bottom-loader SSTOs
  2. Horizontal-landing SSTOs
  3. Un-Crasher TSTOs

I may think of and add additional configurations later if time permits. But next up: Bottom-loader SSTO landers.

Posted in ISRU, Lunar Commerce, Lunar Exploration and Development, Propellant Depots, Reusable Lunar Landers | 8 Comments

Goff Family 2021 Summer Sabbatical Part 1: Utah Trip

Okay, so for the first leg of my sabbatical, we went on a trip to Utah to visit my family. It had been two years since the last time we had seen any of my family in person. Our last trip had been to go be there for my “little” brother’s wedding in the Salt Lake temple. A lot has happened since then, including Jeremy’s wife Emily graduating from BYU, my older brother Adam graduating from Western Governor’s, and Jeremy and Emily having their first baby.

So as early as last December, when it was clear that effective COVID vaccines were soon to be available, we had been notionally planning on going out sometime in May or June. Once Tiff and I had our shots scheduled, we decided to plan something for end of May. Serendipitously, by the time we went to leave, Tiff, Jonny, and I were fully vaccinated, and Jamie and Peter had at least been able to get their first shots. At the time we planned this trip, we had no idea that I was going to be taking the full-time position at Voyager and transitioning out of my Altius role. Once we decided to do that, we set my last day at Altius as the day before we wanted to leave for Utah, and then worked extra hard to make that happen.

I ended up working late my last day at Altius, so we ended up taking an extra day (the 21st) to finish packing and take care of passport things. It turns out that in our part of Colorado, all of the places you can apply for a passport require an advanced appointment to be scheduled, and all of them were booked over a month in advance. With expedited passports taking 4-6wks, and us wanting to leave on our Canada trip by the second week of July, we couldn’t wait that long. Fortunately, Utah didn’t have as much of a backlog, so I scheduled a passport meeting at the civic center for my parent’s town for our third day there. And then of course made it look like on Twitter that the whole Utah trip was some last-second idea we decided to do on a lark as a way to get our passport applications submitted, because silliness.

We had a great time out there, participating in the baby blessing for Jeremy and Emily’s little girl, Victoria, visiting with my family and all of my siblings (and Tiff’s little brother), getting to see Jenny and Alan’s new place they’re remodeling, visiting and getting longsword lessons from my long-time friend Danny Farnsworth (and then later catching dinner with him and his girls), catching lunch and playing pool with Tiff’s “fake adopted sister” and her family, visiting BYU and getting a tour of the new engineering building1, getting to “hike the Y” with Jonny, hiking Bridal Veil falls with the family, a visit to the cemetery on our way out of town, and a side trip to Arches National Park on our way home.

We also got to stay in scenic Parachute, CO because the Eastbound I-70 was closed due to a huge accident in Glenwood Canyon. All the hotels in the town where the road closure started (Rifle) were completely full by the time we got there around midnight, but fortunately we only had to backtrack to Parachute. And we were able to make it home Saturday afternoon.

Anyhow, here are a few pictures from favorite parts of the trip:

Mountain Scenery on our way out to Utah
A great picture Ki caught of Jonny holding Baby Victoria2 after her baby blessing
Someone lost their first mouth stone at the pool party we had at our hotel
Peter and Jamie looking at a sculpture outside the BYU Museum of Art
BYU still doesn’t have an Aerospace Engineering degree3, but between their rocket club, their spacecraft club, and the robotics and UAV groups, they’re heading in a good direction.
Patrick Walton giving us a tour of the new engineering building at BYU. This lab was where his startup, CareWeather built their first satellites
Patrick also showed us the ground stations for BYU’s spacecraft club that they used for their PICSats. For CareWeather’s cubesats they switched to using an Iridium transceiver and had much better success.
On our second-to-last day in Utah, Jonny wanted to “hike the Y” with me. The Y trail is about 2.2mi round trip, and has over 1000ft of elevation change. I think the last time I made this hike was as a freshman at BYU, back when I was Jonny’s age.
The first few sections were pretty brutal, but ultimately we both made it all the way to the top!
Here’s a panoramic view from the top of the Y, looking out over Utah Valley.
That evening, we went to Bridal Veil falls with my mom, my little sister Mary, and Tiff and the boys. Tiff, Jamie, and Pip decided to hike all the way up to the first falls.
A view of the upper falls, with Jamie and Pip
Me, Jonny, and my youngest sister, Mary sitting around the firepit in my parent’s “Secret Garden”
Another view of their Secret Garden
A trip to Utah wouldn’t be complete without a visit to Jarom’s grave. Tiff had the good idea of having us sing a hymn while we were there, so we sang Families Can Be Together Forever. Very apropos.
On our way home, we went to Arches National Park for the first time as a family. It was a lot of fun. Here were the youngest three at the North Window arch.
And here are all the boys, looking silly as usual, in front of the South Window
I think the Double Arch was my favorite one of the park. Interestingly while we were here, I met a Filipino family from Cavite4, and then we ran into a family from our latter-day saint Ward here in Lafayette, CO who were also out on vacation. Small world!
The boys, striking a pose at the Double Arch
Peter and Jamie at the upper viewpoint for the Delicate Arch. We didn’t have enough time (or water!!) to do the hike out to the arch itself.
That night at Olive Garden in Grand Junction, Pip got to have spaghetti with a meatball that was almost the size of his head. If you’re wondering how I did with my calorie budget on this vacation, I believe the best description is the line from Alien “Nuke it from orbit, it’s the only way to be sure!”
With westbound I-70 blocked due to a huge accident up Glenwood Canyon, we had to backtrack to find a hotel. Fortunately we got the last room at the Grand Vista Hotel in Parachute, CO, and didn’t have to drive an extra hour back to Grand Junction. It was a bit crowded, but with the rollaways, we made it work.

Anyhow, that was the first leg of our adventure. We’re now back in Colorado, starting to pack up so we can move out of the house we’ve been renting for the last 8yrs. Tomorrow morning the dumpsters arrive, and Friday we get several of U-haul’s equivalence of the PODS mobile storage units. Wish us luck!

Posted in Family, Friends, Jonny Bloggin, Pip Bloggin | 2 Comments

Transitions and Summer Sabbatical

I imagine most of you who read Selenian Boondocks probably also follow me on Facebook and/or Twitter. But for those of you who don’t, as of May 21st, I decided to move up to a full-time position at my parent company, Voyager Space Holdings, and transitioned out of my role as President and CEO of Altius Space Machines1.

This will be an interesting change, basically moving into more of an intrapreneurial role rather than the entrepreneurial role I’ve been in for most of my career. As the VP of On-Orbit Servicing at Voyager, I’ll be providing leadership for their whole On-Orbit Servicing portfolio, including helping guide Voyager investments/acquisitions in the OOS space, developing and implementing a go-to-market and technology development strategy for Voyager OOS capabilities, and generally leading all things OOS at Voyager.

As part of this transition, I’m taking a 3-month sabbatical to recharge before jumping into my new role2. As part of my “unplugging” efforts, I’ve signed off of social media, unplugged from things work related, and am planning on using this blog as my primary means of communicating with people about my family’s misadventures this summer.

High level plans for the sabbatical include:

  1. A trip to Utah to visit family for the first time in two years (last week).
  2. Packing up and moving out of our current rental (most of June).
  3. Some camping stuff (late June/early July).
  4. A roadtrip to Canada3, the US Pacific Northwest, and possibly Alaska4 (mid July/early August).
  5. Looking for a new house to buy or rent5 in the Denver North area, and getting resettled (August).

My first week back at Voyager should be just in time for Space Symposium in Colorado Springs this August. Between now and then, I’ll mostly be blogging about our travels, but I may do a space blog post or two (not work related) that had been sitting on the backburner due to running a bootstrapped aerospace startup.

Oh, and if you want to comment on the blog posts, please comment here instead of on Twitter. I’m trying to avoid getting sucked into Twitter comments while I’m gone, and will only be on long enough to post a link6.

Posted in Administrivia | 2 Comments

The last few years

john hare

I noticed the other day that it had been over a year since I posted, and at least double that since posting on a space topic. I’ve had a bit going on for distraction, and haven’t had anything new to add in the way of space related concepts.

A few years ago with the recession going away, we started trying to expand the construction company back out to where it was pre-recession. Went through a couple of dozen people trying to expand with no success. Most couldn’t pass a drug test, or didn’t have transportation, or were unreliable, etc etc. Focusing on the company tends to restrict hobbies like blogging about space. I have my core crew and myself with no new people.

Hired an intern (paid) from Florida Polytechnic two years ago for the summer. His job was to work on remote controls for various small equipment we use. If I could not find the people to do the hard work, possibly make the work itself easier. He accomplished nothing useful in three months. Literally nothing. I have been slowly learning to get this done myself. It would be far more efficient if I could hire someone that understands the field, but have failed to find them.

We had a slowdown during the Covid lockdowns last year followed by a slammed schedule from last May through April this year. Slowing down some now with material shortages and difficulties with building departments permitting and inspections.

I got married in February this year and have had other things on my mind. We are buying a lot and will build over the next year mostly with cash. Granddaughter graduated University of Georgia this year with a degree in Biochemical Engineering. (don’t know what that means but she gets a good job right out of school) Other things going on locally.

Noticed a comment on another site that suggested that many of the concepts discussed here have been made obsolete by the success of SpaceX. While I will acknowledge that some of the concepts that made sense in the first place (many didn’t) may be less important, I still believe there is room for improvement all the time. SpaceX may be on the way to becoming the Walmart of space launch, but I believe there are many companies that are well poised to become the Dollar Stores and Discount Auto Parts of space. Those companies may benefit from anything that gives a competitive advantage. One of them may also pass on the outside when we are looking at the infield. As an aside, I am impressed with the progress SpaceX has made, while being very uncomfortable with the “hand it to Elon” meme going around.

I am inclined to restrict my limited blogging to things that are either new, of where I have some experimental evidence on a previous idea. I did an experiment a few years back that seems to support a method of doing the Thrust Augmented Nozzles that Jon wrote up only quite low tech. I have an idea of an inexpensive way to focus sunlight better over long (GEO to surface) distances and will run an experiment or two before discussing. And of course my various pump concepts still fascinate me, but would bore anyone else unless I produce some experimental proofs. Same with compensating nozzles.

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Payload fraction derivation for vehicle with split delta-V (case #1)

Consider a vehicle that undertakes a first $\Delta v$, then picks up a payload and undertakes a second $\Delta v$. It carries the propellant for both maneuvers, but only on the second maneuver does it have the added mass of the payload. This situation might be representative of:

1. a one-way lunar vehicle, arriving in low Earth orbit fully fueled but with no payload. It executes a trans-lunar injection burn and then a lunar orbit insertion burn, all with no payload. It then picks up a payload in lunar orbit and descends to the surface with the payload and lands with essentially all its propellant expended.

2. a reusable lunar lander, based on the surface of the Moon, fully fueled by lunar propellant but lacking any payload, which ascends to a lunar orbit and recovers a payload in that orbit, then descends to the surface, landing with nearly all its propellant expended.

3. a space tug that departs for geosynchronous orbit and recovers a satellite, then returns with it to a low-Earth orbit for repair.

First, define the mass conditions at the beginning and end of $\Delta v_1$:

(1)    \begin{equation*} \eta_1 \equiv \exp(\Delta v_1/v_e) = \frac{m_\text{vehicle} + m_\text{prop1} + m_\text{prop2}}{m_\text{vehicle} + m_\text{prop2}} \end{equation*}

Alternatively, and just as importantly, the conditions bracketing $\Delta v_1$ can be described in terms of an initial mass:

     \begin{displaymath} \eta_1 = \frac{m_\text{initial}}{m_\text{initial} - m_\text{prop1}} \end{displaymath}

This expression can be conveniently rearranged to yield the propellant mass consumed by the vehicle in $\Delta v_1$:

     \begin{displaymath} m_\text{prop1} = m_\text{initial} \left(1 - \dfrac{1}{\eta_1}\right) \end{displaymath}

In a similar manner, we define the mass conditions at the beginning and end of $\Delta v_2$:

(2)    \begin{equation*} \eta_2 \equiv \exp(\Delta v_2/v_e) = \frac{m_\text{vehicle} + m_\text{payload} + m_\text{prop2}}{m_\text{vehicle} + m_\text{payload}} \end{equation*}

We can also express the conditions bracketing $\Delta v_2$ in another way, in terms of initial mass:

     \begin{displaymath} \eta_2 = \frac{m_\text{initial} + m_\text{payload} - m_\text{prop1}}{m_\text{initial} + m_\text{payload} - m_\text{prop}} \end{displaymath}

Yet another approach will later yield a useful relationship:

     \begin{displaymath} \eta_2 = \frac{m_\text{initial}/\eta_1 + m_\text{payload}}{m_\text{vehicle} + m_\text{payload}} \end{displaymath}

     \begin{displaymath} \eta_2\left(m_\text{vehicle} + m_\text{payload}\right) = m_\text{initial}/\eta_1 + m_\text{payload} \end{displaymath}

     \begin{displaymath} \eta_2 m_\text{vehicle} + \eta_2 m_\text{payload} = m_\text{initial}/\eta_1 + m_\text{payload} \end{displaymath}

     \begin{displaymath} \eta_2 m_\text{vehicle} + (\eta_2 - 1) m_\text{payload} = m_\text{initial}/\eta_1 \end{displaymath}

     \begin{displaymath} m_\text{initial} = \eta_1\eta_2 m_\text{vehicle} + \eta_1(\eta_2 - 1) m_\text{payload} \end{displaymath}

The propellant mass consumed by the vehicle in $\Delta v_2$ can also be expressed in a manner analogous to prop1:

     \begin{displaymath} m_\text{prop2} = \left(1 - \dfrac{1}{\eta_2}\right)\left(\dfrac{m_\text{initial}}{\eta_1} + m_\text{payload}\right) \end{displaymath}

     \begin{displaymath} m_\text{prop2} = m_\text{initial}\left(\dfrac{1}{\eta_1} - \dfrac{1}{\eta_1\eta_2}\right) + m_\text{payload}\left(1 - \dfrac{1}{\eta_2}\right) \end{displaymath}

Now we are positioned to calculate the total propellant load:

     \begin{displaymath} m_\text{prop} = m_\text{prop1} + m_\text{prop2} \end{displaymath}

substituting the definitions for prop1 and prop2

     \begin{displaymath} m_\text{prop} = m_\text{initial} \left(1 - \dfrac{1}{\eta_1}\right) + m_\text{initial}\left(\dfrac{1}{\eta_1} - \dfrac{1}{\eta_1\eta_2}\right) + m_\text{payload}\left(1 - \dfrac{1}{\eta_2}\right) \end{displaymath}

collecting terms and simplifying

     \begin{displaymath} m_\text{prop} = m_\text{initial} \left(1 - \dfrac{1}{\eta_1} + \dfrac{1}{\eta_1} - \dfrac{1}{\eta_1\eta_2}\right) + m_\text{payload}\left(1 - \dfrac{1}{\eta_2}\right) \end{displaymath}

(3)    \begin{equation*} m_\text{prop} = m_\text{initial} \left(1 - \dfrac{1}{\eta_1\eta_2}\right) + m_\text{payload}\left(1 - \dfrac{1}{\eta_2}\right) \end{equation*}

now let us define the vehicle’s “dry” mass entirely in terms of initial-mass-sensitive ($\phi$), propellant-mass-sensitive ($\lambda$), and payload-mass-sensitive ($\epsilon$) mass terms. This is a substantial simplification, but it should do for now.

     \begin{displaymath} m_\text{vehicle} = \phi m_\text{initial} + \lambda m_\text{prop} + \epsilon m_\text{payload} \end{displaymath}

     \begin{displaymath} m_\text{initial} = \eta_1(\eta_2 - 1)m_\text{payload} + \eta_1\eta_2 m_\text{vehicle} \end{displaymath}

substituting the definition of the vehicle’s mass in

     \begin{displaymath} m_\text{initial} = \eta_1(\eta_2 - 1)m_\text{payload} + \eta_1\eta_2(\phi m_\text{initial} + \lambda m_\text{prop} + \epsilon m_\text{payload}) \end{displaymath}

we collect terms related to the initial mass on the left hand side

(4)    \begin{equation*} m_\text{initial}(1 - \phi\eta_1\eta_2) = m_\text{payload}(\eta_1(\eta_2 - 1) + \epsilon\eta_1\eta_2) + \lambda\eta_1\eta_2 m_\text{prop} \end{equation*}

Take equation(3) and multiply it through by $\lambda\eta_1\eta_2$:

     \begin{displaymath} \lambda\eta_1\eta_2 m_\text{prop} = \lambda\eta_1\eta_2 m_\text{initial} \left(1 - \dfrac{1}{\eta_1\eta_2}\right) + \lambda\eta_1\eta_2 m_\text{payload}\left(1 - \dfrac{1}{\eta_2}\right) \end{displaymath}

     \begin{displaymath} \lambda\eta_1\eta_2 m_\text{prop} = m_\text{initial} \left(\lambda\eta_1\eta_2 - \dfrac{\lambda\eta_1\eta_2}{\eta_1\eta_2}\right) + \lambda\eta_1\eta_2m_\text{payload}\left(\dfrac{\eta_2 - 1}{\eta_2}\right) \end{displaymath}

(5)    \begin{equation*} \lambda\eta_1\eta_2 m_\text{prop} = m_\text{initial} \left(\lambda\eta_1\eta_2 - \lambda\right) + m_\text{payload}\lambda\eta_1(\eta_2 - 1) \end{equation*}

then substitute the RHS for equation(5) in equation(4) and collect terms

     \begin{displaymath} m_\text{initial}(1 - \phi\eta_1\eta_2 - \lambda\eta_1\eta_2 + \lambda) = m_\text{payload}(\eta_1(\eta_2 - 1) + \epsilon\eta_1\eta_2 + \lambda\eta_1(\eta_2 - 1)) \end{displaymath}

further simplifying

     \begin{displaymath} m_\text{initial}(1 - (\phi + \lambda)\eta_1\eta_2 + \lambda) = m_\text{payload}(\eta_1(\eta_2 - 1)(1 + \lambda) + \epsilon\eta_1\eta_2) \end{displaymath}

With all terms relating only to initial mass and payload mass, a general expression for payload fraction can at last be defined:

     \begin{displaymath} \dfrac{m_\text{payload}}{m_\text{initial}} = \dfrac{1 - (\phi + \lambda)\eta_1\eta_2 + \lambda}{\eta_1(\epsilon\eta_2 + (\eta_2 - 1)(1 + \lambda))} \end{displaymath}

Posted in Rocket Design Theory | 2 Comments

An Updated Propellant Depot Taxonomy Part VI: Roving Depots

In the last post in this series, I discussed the idea of large-scale depots for human spaceflight applications, which operate in fixed, low-orbits. While the final post in this series will investigate human spaceflight depots that operate in fixed higher orbits1, in this post I want to talk about situations where you want to refuel with large amounts of cryogenic propellants in an orbit where a permanent depot doesn’t make sense — in temporary high-elliptical orbits on your way into/out of a deep gravity well like Earth’s. The background on these depots involves getting into the weeds on some orbital dynamics, but I’ll try to keep it as understandable as possible for the layperson2.

Orbital Dynamics Background for Roving Depots

For an outbound interplanetary mission, there are two obvious places to do refueling — one at the first safe stopping point after leaving the planetary body3, and other is in an orbit that’s just shy of leaving the planetary body’s gravity well4. For a high-thrust/low-Isp departure, like you’d have with a chemical or nuclear thermal rocket, this would be a highly elliptical orbit, with the periapsis as low as possible5, and a apoapsis as high as practical6. There’s just one problem — in order to leave on an interplanetary trajectory from a highly elliptical orbit, that elliptical orbit’s periapsis has to be in the right place7, going in the right direction8, at the right time9. As you can probably guess, the odds of a specific highly elliptical orbit for one interplanetary departure trajectory lining up with another specific interplanetary departure trajectory at a specific point in the future is really, really low.

An illustration of hyperbolic departures, showing the locus of periapses/injection points on the opposite side of the earth from the desired departure asymptote (credit: Bate, Mueller, and White)

While I was working with Mike Loucks and John Carrico on our three-burn departure orbital dynamics papers (reviewed previously on Selenian Boondocks here, here, and here), I realized that there might be a way around this problem of elliptical orbits not lining up for future missions, especially if you had a reusable, mobile depot capable of both entering into and then returning from that highly elliptical orbit.

Illustration of the 3-Burn Departure method described in the two linked AAS papers. An interplanetary mission stack (1) starts in a low-orbit depot’s orbit after topping-up, (2) performs a burn to enter a highly-elliptical phasing orbit, (3) performs a plane change maneuver at apogee to align the departure plane, and (4) performs the final interplanetary departure burn when the spacecraft is back at perigee in the right place at the right time.

One or more such “roving depots” could work with reusable tankers10 and a low-orbit depot to preposition propellants into a highly-elliptical orbits for specific departure missions, with the mission stack for a given mission only having to travel out and rendezvous with the depot on the last time the departure highly-elliptical orbit plane lines up with the low-orbit depot’s plane. Once the mission stack has refueled, and left the roving depot (on its way to doing its final plane change and departure burn), the roving depot can return to the low-orbit depot the next time its plane lines up with the low-orbit depot, enabling it to be refueled and prepared for its next mission.

Conceptual Illustration of a reusable space tug. A roving depot would likely look similar, except possibly with more tankage and robotics capabilities. (Credit: Commercial Space Development Company)

Roving Depots

Application: Significantly enhancing the performance benefits of using a low-orbit depot, by providing one last chance to top off before heading out into interplanetary space. This can range from topping up a smallsat interplanetary stage to assembling and fueling a large interplanetary human mission or multi-ship convoy.

Location: As described earlier, roving depots are mobile depots that start a given mission at a low-orbit depot, maneuver into a highly elliptical orbit that is targeted for a specific interplanetary departure, and then returns to the low-orbit depot after the refueling operation is over.

Size: Depends strongly on what is being refueled. These could be as small as 100’s of kg for refueling a smallsat launcher interplanetary stage, up to 10’s to 100’s of mT for refueling larger human spaceflight missions.

Propellant Types: The propellant type for a roving depot will be driven by the propellant type used for the mission stack stage that is performing the interplanetary injection. For smallsat interplanetary stages, this is almost certainly storable, while for human spaceflight missions this would likely be LOX/LH2 or LOX/CH4.

Other Considerations

  • For roving depots and tankers operating around planets with an atmosphere, you’ll almost always want to use some form of aerobraking or aerocapture system11. Because you want your highly-elliptical orbit to have a relatively low periapsis for departure performance reasons, it only takes a little burn at apoapsis to lower the periapsis far enough for practical aerobraking/aerocapture.
  • Something you may have noticed is that the distinction between a roving depot and a tanker is sort of blurry. As I see it, they exist in sort of a continuum with expendable tankers on one end and reusable roving depots on the other extreme. The key differences are that roving depots would be more likely to have more significant propellant cooling (active and passive) capabilities, likely be designed to handle a wider range of client vehicles, and likely carry a lot more rendezvous, prox-ops, and grappling hardware.
    • I think the tankers that top off a roving depot in its mission orbit would likely be just minimalist upper stages with an aerocapture system, with as much of the smarts and complexity offloaded to the roving depot as possible. Minimizing the dry mass per unit propellant hauled from the low-orbit depot to the roving depot.
    • I think the roving depots, since they move less would strike a balance of complexity/robustness between the tanker and a fixed depot. You don’t want to go too crazy by throwing dry mass at problems like RPOD12 reliability, and mission robotic flexibility, but you want to be able to make the tankers as dumb and lean as possible, by offloading capabilities to the roving depot as much as possible.
  • This idea of roving depots can be combined with in-space assembly/manufacturing in the highly-elliptical orbit, sending up parts/materials/propellant for the mission every few months when the low-orbit depot lines up with the departure plane, assembling the overall stack, and then only sending the mission crew up on the last time the low-orbit depot’s plane aligns with the departure plane.
  • For chemical propulsion, travel to interplanetary destinations like Mars and Venus typically is only feasible once every 1.5-2yrs (depending on the synodic period). The use of roving depots can allow you to spread out the propellant launches for missions to a planet like that over a longer period of time. Instead of having to launch all the propellant and hardware for a given “launch season” all in the few months leading up to that season, you may be able to set up multiple roving depots, aligned for that departure opportunity, and then top them up over the course of a year or more. This allows a much smaller fixed low-orbit depot to support a lot more mission capacity than you would otherwise think, because the low-orbit depot wouldn’t need as much surge capacity, since you could likely plan things in advance.
    • This also suggests to me that for busy planetary systems like Earth, if roving depots take off as a concept, they’d likely significantly outnumber the low-orbit fixed depots.
  • One drawback to using roving depots and these highly elliptical parking orbits is that you end up putting a lot more van allen belt passes on your hardware than you would otherwise. While you typically won’t have your crew onboard until late in the process, your electronics, especially on your roving depot, will take a lot more radiation than it might otherwise.
  • On the plus side, you spend a lot less time in LEO where MMOD13 issues are worse, so your mission hardware doesn’t need as much MMOD shielding for how long it is in orbit. Additionally, since you spend most of your orbit far away from the planet, these highly-elliptical phasing orbits tend to be much easier for long-term cryogenic thermal storage.
  • One other consideration is that the longer you spend in the phasing orbit, the more orbit adjustment maneuvers you’ll need to perform. This may put some limitations on how long you can practically build things up in a phasing orbit for a given mission. If you’re just pre-staging propellant long in advance for a large convoy mission, you may be able to let your orbit drift a bit, and only trim things up shortly before departure, but we’d need to run the numbers on how practical that is. This is more of the case for orbits with very high apogees/long periods, especially in multi-body systems like the Earth/Moon system where, lunar perturbations become more of a problem with high apogee phasing orbits. In theory, it may be possible to craft an orbit that starts in a lower, shorter-period phasing orbit initially, but that then boosts up to a higher phasing orbit shortly before the final refueling of the mission stack. Long story short, there are lots of knobs to twist on optimization14.
  • One other problem I’m handwaving away as probably solvable is the complexity of rendezvousing with a roving depot in a highly-elliptical orbit. This will definitely be a lot different than the relative dynamics of rendezvous with objects in LEO. Though fortunately this should be pretty similar with trying to rendezvous with a facility in NRHO, so it’s something that probably has had a lot of recent thought put into it.
  • Roving depots around planets with lots of moons will definitely be more challenging from an orbital dynamics standpoint, but could be really enabling for missions to the gas giant planets. Especially if you want to do return trips, and don’t have something as cool as an Epstein Drive available yet. In some ways this reminds me of the idea of using base camps and/or storage depots when planning expeditions up mountains, or the early Antarctic expeditions. Once you have the right building blocks in place, there’s a lot you can do.

When you think about what you can do with the combination of low-orbit depots and roving depots on both ends of the mission, especially supported with ISRU and reusable launch, you can actually do very large and capable missions without needing super-heavy lift vehicles. It’s kind of amazing what you can do with a refuel early, refuel often, reusable space transportation architecture.

Next Up An Updated Propellant Depot Taxonomy Part VII: Human Spaceflight Fixed Depots (High-Orbit)

Posted in Commercial Space, ISRU, Launch Vehicles, Lunar Exploration and Development, Mars, NASA, NEOs, Orbital Dynamics, Propellant Depots, Space Development, Space Exploration, Space Transportation, ULA, Venus | 10 Comments

An Updated Propellant Depot Taxonomy Part V: Human Spaceflight Fixed Depots (Low-Orbit)

For this next depot taxonomy post, we’ll finally be talking about what people usually think about when they hear the term orbital propellant depot — larger, cryogenic refueling facilities, focused on enabling large-scale human spaceflight missions, performed by a diverse variety of users, and going to/from a wide variety of destinations. The idea for such propellant depots for enabling interplanetary human spaceflight dates back to at least 1928 with the writings of Guido von Pirquet1.

Concept illustration for a LEO Depot and reusable space tug (Credit: Cislunar Space Development Company)

This blog post will be focused on what I call “Low-Orbit” human spaceflight depots. These are depots located near the lowest stable orbit around a planetary body. This is the first place at which you can realistically refuel or switch vehicles on your way from a planetary body, and is the last place at which you can refuel or switch vehicles on your way down. As a firm believer in the idea of refueling early and refueling often, low-orbit depots are an important piece of infrastructure for any planetary system humanity wants to travel to/from regularly. A later blog post in the series will talk about “High-Orbit” depots — depots operating in fixed locations2 located out near the edge of a planetary system’s gravitational sphere of influence, and will include a discussion of where those types of depots might make sense.

Before we jump into the weeds about low-orbit human spaceflight depots, I did want to address a recent train of thought I’ve seen that suggests that just using tankers and directly refueling a vehicle is superior to having a depot involved. While this could easily be the topic of a series of its own, I wanted to briefly highlight a few of the biggest advantages I can see of having a depot vs just using direct refueling with tankers:

  • Flexibility: A depot, properly designed, with published, standardized grappling, refueling, and power-data interfaces, can be agnostic about who it gets propellant from and who it sells propellant to. Depots can quickly take advantage of whatever the cheapest source of propellant is at a given time (RLVs, ISRU, propellantless launch, buying leftover capacity from other missions going to destinations near a depot, atmospheric gathering, etc), and can easily service both smaller missions and bigger ones. Tanker-based approaches tend to be a lot less adaptable, typically being optimized for one or two specific vehicles that needs refueling.
  • Robustness: With a fixed installation, that only has to be launched once for a long mission lifetime, you can afford to throw way more resources (dry mass, volume, and power) at making rendezvous, prox-ops, docking (RPOD), and manipulation as safe and reliable as possible. This could include beacons, larger more capable (and/or redundant) relative navigation sensors and comms, longer reach capture robotics that minimize the dry mass requirements on tanker and client vehicle alike, etc.
    • For tankers, on the other hand, you want to minimize parasitic dry mass that has to be launched every time, and for the departing vehicle you want to minimize mass you have to carry through large, high delta-V in-space maneuvers. You could in theory carry a nicer RPOD kit on your departing vehicle that you jettison before leaving LEO, but now you’re amortizing that mass and cost over a much smaller number of missions, or starting to add more complexity than just doing a depot.
    • Another question to ponder is with vehicles that require large numbers of refueling events per mission, is it best to have the client vehicle handle all of those docking maneuvers with its (by definition) less-capable RPOD capabilities? With a depot, each tanker and each client vehicle only has to perform one mission-critical RPOD/refueling operation per mission, whereas with direct refueling via tankers, the client vehicle would typically have to perform a larger number of mission-critical RPOD events. A depot would also have to handle the same larger number of RPOD/refueling events, but as mentioned before, can throw more resources at making these as reliable and safe as possible.
    • Longer refueling cycles from using a direct-tanker refueling approach also increases the MMOD3 risk to the departing vehicle, which by definition can’t afford to throw as many resources at MMOD protection as a depot can.
    • A corollary to this is that depots make the most sense if you use them in a way that offloads as much of the refueling-unique hardware/software as possible from the delivery and client sides of the system to the depot. Ideally a tanker would be a minimally modified upper stage4, and client vehicles would also have similarly minimalistic hardware needed to be grappled and receive propellant. If you’re doing your delivery vehicle or your client vehicle in a way that makes you question the utility of a depot, that may be a hint that you’re doing something wrong.
  • Non-Integerality: Yes I may have made up that word, but the point is that tankers tend to come in integer quantities. Unless you always design your departing vehicles to use only integer quantities of tankers, you’ll almost always end up having wasted propellant. This is especially true given how launch vehicles, and in-space vehicles tend to increase performance and get upgraded over time, and don’t necessarily upgrade at the same rates. If you only ever had a monopoly/monopsony situation where you only had one tanker provider, and only one vehicle needing tankers, you might be able to keep tanker size locked to an integer fraction of the amount of propellant needed, but in reality that isn’t going to happen. So a tanker-based system is always going to end up wasting propellants, and this is even more the case when you have diverse customer vehicle and delivery vehicle sizes. The more diversity you have in your space transportation ecosystem, the more a depot makes sense.

There are probably other good arguments I’m glossing over, but long-story short, unless you’re interested in a boring monoculture world where only one type of in-space transportation system exists, depots make a lot of sense. So, without further ado, let’s jump into some of the taxonomical considerations of human spaceflight low-orbit depots.

Lockheed Martin concept for an orbital Mars Base Camp with refueling capabilities for their reusable Mars landers in Low Mars Orbit (credit: Lockheed Martin)

Human Spaceflight Low Orbit Depots

Application: Refueling large transfer stages or in-space transports for ferrying people and cargo between LEO, the Moon, Mars, Venus, and other destinations of interest.

Location: As discussed earlier, this blog post is focused on depots located near the lowest practical stable orbit around a planetary body. Details vary for different planetary bodies, as described below5:

  • For Earth, the low-orbit depot location is in LEO, ideally in the lowest inclination that still lets you hit required departure asymptotes and maximize the number of economically useful launch sites to send propellant, people, cargo, and materials to/from the depot6. You probably only need one or two such low-orbit depots, though if you get to high-enough earth departure throughput there may eventually make sense to spread more depots out at different RAANs7. Likely for a first human spaceflight depot, as with the previously discussed smallsat launcher depots, you’ll want to locate it in LEO near other human-occupied facilities like ISS — far enough away to be safe, but close enough to conveniently move between each other, ideally within one work shift8.
  • For a low-orbit depot around the Moon, this would likely be a polar or near-polar LLO9, though due to the very slow rotation and practically zero J2 perturbation10, if you have a lot of non-polar surface sites, you eventually may want multiple smaller depots in equally RAAN-spaced near-polar LLO planes, and maybe one in an equatorial orbit. If you’re trying to do lunar surface missions, having your depot in LLO makes way more sense than in a higher orbit like NRHO, for reasons I should probably go into in another blog post.
  • For Mars this would also likely be a LMO orbit, with an inclination high enough to be able to access any points of interest on the surface, while still being low enough to minimize delta-V penalties11, and keep the nodal precession rate fast enough to minimize phasing orbit time for three-burn departures. You’ll likely also have to put some thought into perturbations from Phobos and Deimos12.
  • For Venus, the extremely low rotation speed and therefor very low J2 pertubation may require you to do multiple smaller depots in similar inclinations but equally RAAN-spaced planes, as you won’t pass over a given point on the surface very frequently, and the very slow nodal precession rate could potentially require very very long phasing orbits for a 3-burn departure. Venus has a deep enough gravity well that you do want to refuel in LVO coming to/from, but it’s not trivial from an orbital dynamics standpoint13.

Size: As big as you can practically get away with — ideally you’d want this depot to be at least 2x the propellant capacity as whatever the largest vehicle you’re refueling. So somewhere in the 100-2000mT range, or even bigger14. Early versions will want to be single-launch if possible, in many cases repurposing at least one of the main propellant tanks from the stage that delivered them to their destination as one of the depot tanks15. Eventually, it may be possible to do multi-tank depots, but if you can do a single launch depot big enough for refueling two missions, you may be better off making more than one depot instead of trying to make the depot super big.

Propellant Types: For low depots, you’re primarily going to be dealing with large transfer stages (Centaur V, Starship, New Glenn Upper stage), which typically use LOX, and either Methane or LH2 for the fuel. Most of these use autogenous pressurization, and use the main propellants for RCS. So most of the depot will be for LOX, LH2, and/or Methane.

  • For Mars or Venus you may eventually also want to store liquid CO for some applications, since it’s an easier ISRU propellant, but that remains TBD.
  • A lunar low-orbit depot may also want to stock storable propellants, depending on what lander propellants end up being most popular16.
  • You may eventually also want to store some secondary fluids (Helium or Neon for active cooling loops, life support consumables like water, air, etc), but you may not explicitly need a depot for that function.

Some Other Considerations for Human Spaceflight Low-Orbit Depots

  • As mentioned before, human spaceflight depots want to be designed in a way to enable offloading as much of the RPO and docking/or berthing from the vehicles they’re servicing. The less parasitic dry mass that tankers and clients have to lug around on every mission, the better.
  • Storing cryogens in low orbits tends to be hard — you have a warm planet blocking half of the sky. So launching the propellant in a subcooled state or even partially frozen (i.e. slushy propellants) can help a lot. Also a lot should be done to minimize heat leaks between the cold part of the depot and any hot sections (habitation, power, etc). If you can’t get to zero boiloff, LH2 is a great thermal sponge, and can be used to chill other propellants, and intercept heat from heat sources before being vented. You may have to vent some hydrogen boiloff, but if you’re smart, you can use that hydrogen boiloff on the way out to eliminate boiloff issues for everything else.
  • These depots are also big debris targets17. Deployable MMOD/MLI18 solutions could be very helpful to avoid a puncture, which would probably be very hard to patch. Since these depots are fixed, and are typically only performing stationkeeping maneuvers, it may be possible to augment their MLI/MMOD protection over time using in-space assembly/manufacturing techniques19.
  • Especially for low-orbit depots around the Moon/Mars/Venus, there may be a benefit to having some temporary habitation/shelter collocated with the depot, especially if you’re supporting multiple sites, as a search and rescue option during exploration phases, and as a stop-over point to act as a buffer between different sizes of transportation between planets and between the depot and the surface.
  • Over time you may want to add in other facilities such as dry docks for assembling, and repairing/maintaining large in-space vehicles/structures, habitation facilities, etc. But they should probably be coorbital, near the depot, not attached (as that will make cryo thermal management all the harder, and the depot is a big hazardous work location, where you should probably minimize the amount of time people spend in close proximity to it). This could be done in two ways — coorbital facilities, spaced where the safe time to travel from one to the other is as short as practical (definitely less than an 8hr work shift if at all possible, and much closer if possible), or by having the two facilities connected by a connecting tether or other structure that includes elevator facilities.
    • If your depot facility starts wanting to have permanent collocated habitation (say for in-space assembly/repair/maintenance of in-space stages), and having the two be coorbital doesn’t work, you’re likely going to want to keep the people separated as far away from propellant tanks as possible, both to minimize heat-leak into the tanks, but also to minimize hazard to the people20.
    • For larger depots, and ones where people will be there more, putting some thought into spatially separating the fuels and oxidizers more could be a good idea. In rockets you often can’t do much to keep the two separated, and many use a common bulkhead, but in a fixed facility it’s more of a possibility. Having fuel and oxidizer that close together for long periods of time is somewhat tempting fate — you kind of have to do it for high efficiency rockets, but there’s something to be said for having your fuel and oxidizer many meters apart for a long-duration facility.
  • One area of disagreement I have with other depot advocates is whether propellants should be shipped to a depot as cryogenic propellants (LOX/LH2/LCH4), or if you should ship them as something more storable like water and CO2, and have the depot itself have large-scale electrolyzing, separation, and propellant refrigeration systems. My concern is that while in theory very large solar arrays could be done in space, combining large flexible structures like multi-MW solar arrays and radiators with a facility that sees a lot of docking, propellant slosh, etc seems like a bad idea from a structural dynamics standpoint. Also depots with very large power generation and heat rejection capabilities are likely to come later in the process, since they’ll almost certainly require multiple launches and in-space construction.

Anyhow, I probably could go on, but as with the previous parts of this series, I am only trying to scratch the surface with considerations and operating details, as I introduce each new type of depot. This definitely isn’t the last you’ll hear from me on the topic.

Next-Up An Updated Propellant Depot Taxonomy Part VI: Roving Depots

Posted in Blue Origin, Commercial Space, Launch Vehicles, Lunar Commerce, Lunar Exploration and Development, Mars, NEOs, Orbital Dynamics, Propellant Depots, RLV Markets, Space Development, Space Exploration, Space Transportation, SpaceX, ULA, Venus | Tagged , , , , , , , | 13 Comments

An Updated Propellant Depot Taxonomy Part IV: Smallsat Launcher Refueling Depots

After a brief hiatus, I’d like to continue this series with the type of depot I’ve spent the most time thinking about over the last several years, and the first type of depot that really fits the mold of what people typically think of when they hear the word propellant depot–depots focused on refueling smallsat launcher upper stages. Before I get into the details of expected characteristics and considerations of this type of depot, I’d like to give some backstory on what led me to thinking of this type of depot1.

For those of you who haven’t been neck deep in the politics around propellant depots over the past decade and a half, suffice it to say, large-scale depots focused on human spaceflight missions have excited more than their fair share of political opposition. Because of that, I started looking at other situations where cryogenic propellant depots could make economic sense independent of any change in the political dynamics around depots for human spaceflight2. Of several potential economically-viable depot markets, the one that I became most interested was in using depots to support sending small satellites to destinations beyond LEO.

Over the past two decades, there has been a steady and now rapid increase in the utilization of satellites smaller than 500kg (“smallsats”) in LEO, driven in part by the continuing miniaturization of electronics and sensors, new manufacturing techniques, and increasing rideshare and dedicated launch capabilities. We’re now also starting to see interest in sending smallsats further afield, with some companies doing GEO smallsats for serving smaller GEO telecom markets and Bringing into Use applications3, and even several groups working on interplanetary smallsats missions to the Moon, Mars, Venus, and beyond. One of the biggest challenges with beyond LEO smallsat missions is that almost all of the options for getting smallsats to destinations beyond LEO suck.

Specifically, here are some of the current options for launching smallsats beyond LEO and some of their limitations:

  • Rideshare: If you’re going to a popular enough orbit, sometimes you can hitch a ride as part of a bigger mission. Unfortunately, as a secondary payload, you have little control over the timing, you can only go to places where others are going (or get dropped off along the way)4, and there are often lots of restrictions and added scrutiny of secondary payload propulsion systems. If you’re going someplace unpopular, rideshare may at best modestly reduce the amount of delta-V your spacecraft has to produce.
  • Buy a Bigger Flight: You could also just secure a larger flight than you need, like say on a Falcon 9, and try to sell the rest of the space. But then you’re stuck herding cats, and if one of them isn’t ready on time, you may have to foot more of the bill if you can’t afford to delay the mission5. And selling the rest of the space only works if you can find an orbit you can drop people off in along the way that they actually want to go to, which can add additional mission constraints to an already complicated mission.
  • Make a High Delta-V Smallsat: You could also just try to make a really high performance smallsat, maybe with staging, drop tanks, and/or an electric propulsion system. But in most of these cases, your propulsion system now dominates your satellite, the amount of net usable payload may be very sensitive to even modest mass growth in your propulsion system, and in the case of EP systems, you may dramatically add to the amount of time it takes to get to your destination.
  • Fly on a Dedicated Smallsat Launcher with a Third Stage: If your payload is small enough, many of the dedicated smallsat launchers are now either offering or contemplating the use of a small chemical or EP third stage. RocketLab for instance can send 15-40kg net to destinations beyond LEO. But the cost in $/kg delivered to the destination can be >$400k/kg.

From talking with at least a few developers of beyond LEO smallsats, what would be nice would be a way to launch your satellite on a dedicated mission that was reasonably right-sized for your spacecraft, with a propulsion system that could get you to your desired orbit as quickly as possible, while minimizing the propulsion requirements on your satellite. And that’s where Smallsat launcher refueling depots come in.

I’m including this Artist’s Conception of a Smallsat Launcher Refueling Propellant Depot Again, Because It’s Awesome, and Because I Can (Credit: Brian Versteeg)

Smallsat Launcher Refueling Depots

Application: Refueling the upper stages, kick stages, and payloads launched by smallsat launchers, for sending dedicated, on-demand missions beyond LEO to MEO, GEO, Cislunar space, or interplanetary destinations.

Location: LEO, likely a singular station (or a small number of stations), ideally at a low altitude (<500km), mid-inclination, and near where other missions are going to. My current favorite location is in an ISS-trailing ~400km x 51.6 degree orbit, trailing as closely as NASA will allow (hopefully <200km behind).

  • The moderate inclination is to maximize the range of interplanetary departure declinations that can be hit6, without being too high of inclination for practically getting to GEO or equatorial MEO destinations.
  • For deep space departures, you’d prefer to have your perigee at departure be as low as possible, to maximize the benefit of the oberth effect. Also for most smallsat launchers the LEO payload falls off somewhat rapidly. But on the other hand you don’t want to be so low that you’re having to waste a lot of propellant on stationkeeping for your depot. 400km like ISS is a reasonable tradeoff.
  • Picking an orbit where many other missions are going to, like an ISS-like orbit, potentially enables buying excess propellant from those other missions. As it is, most missions to the ISS massively underutilize the mass capacity of the launch vehicles, meaning there is potential for buying leftover propellant from commercial crew/cargo launches. Because the primary customer has paid for the whole mission, selling this leftover propellant would be pure profit for the launch operator, potentially enabling pretty interesting price points.

Size: At least 5-10mT capacity, maybe up to 20-40mT on the high end.

  • You want something small enough to launch on a single launch, either as a secondary payload on one of the larger launch vehicles, or as a dedicated launch on one of the larger smallsat launchers (Relativity, Firefly, ABL, etc.)
  • You’d like enough propellant capacity to handle at least 2-3 missions with your largest customer, because mission demand may not be well synchronized with when you can get propellant especially if you’re buying excess propellant from ISS missions.
  • Ideally you want to be bigger than the excess propellant capacity of say a Falcon 9 Dragon mission to ISS, or an Atlas or Vulcan mission with other crew/cargo vehicles, so you can buy as much propellant as possible when its available.

Propellant Types: LOX plus Kerosene and maybe Methane for the upper stages, some form of storable bipropellant for the kick stages and payloads, and helium for pressurization.

  • Most of the existing smallsat launchers use LOX plus a hydrocarbon propellant (mostly Kerosene, but with a few looking at Methane) for their main stages, and some form of storable bipropellant combo (many using HTP plus some sort of hydrocarbon) for the kick stages. Exactly which storable propellant combos get settled on will likely be driven by which companies first start taking this type of depot most seriously.
  • Even though LH2 is almost certainly not a propellant smallsat launcher customers are likely to buy anytime soon, buying some leftover LH2 from a Vulcan or other LOX/LH2 upper stage might still be useful as an expendable coolant to supercool the other cryogens, potentially eliminating cryogenic boiloff potentially without requiring active cooling if you can get LH2 frequently enough.
  • For the helium, it might be worth trying to recover the helium from the upper stages being refueled, removing any oxidizer/fuel trace impurities, and recompressing it. In that way you wouldn’t actually need much helium other than to make up for losses and cold-gas usage on the upper stages. The helium you’ll likely want to try to keep as cold as possible, to make storage easier, so you likely want to have it in close thermal contact with the LOX or methane tanks. though for safety reasons you might not want the helium tanks inside the LOX tanks.

Other Considerations for Smallsat Launcher Refueling Depots

  • You’ll almost certainly want to design the depot to last as long as reasonably possible. This will likely drive you to make the depot robotically serviceable with deliberate modularity for likely wear components.
  • This class of depots will almost certainly be designed for purely robotic operation, without any human habitation capabilities. Though you might want to make the serviceability designed for both robotic and manual servicing. Maybe.
  • You’ll almost certainly want to have your depot repurpose at least one of the main propellant tanks of the upper stage that launches the depot, once the depot has been delivered to orbit. As I’ve shown in previous papers, this is a great way to get free depot tankage capacity. If the depot was launched as a secondary payload on Vulcan, you could get up into the ~40mT capacity for LOX and Kerosene if you wanted to.
  • You’ll almost certainly want to have a fairly capable capture and manipulation robotics capability, with RPO sensors on-board. The goal is to offload as much requirements-wise from the customer upper stages/kick stages to the depot as possible. My personal preference has been to see if the customer smallsat launcher upper stages/kick stages can maneuver their stack adequately to do a drift-by near-rendezvous7 close enough that one or more deployable capture arms can magnetically grapple and retract the stacks — ie avoiding trying to make the smallsat launcher stacks capable of full RPO/docking maneuvers, while also trying to see if you can avoid the depot having to do rendezvous maneuvers in nominal cases. The depot is probably the much heavier of the two vehicles/stacks, so it’s more efficient to have the smaller vehicle move, but you want to do it with the least mods to a stock upper stage–ideally just grapple and refueling ports, and an upper stage capable of being remotely guided by the depot8.
  • Most upper stages and kick stages have RCS thrusters that enable at least 3-axis attitude control. Most upper stage engines also likely have a cold gas purge function to blow excess propellant out of the engine prior to a relight (to avoid the risk of a hard start). It may be possible to use such a cold gas purge with the main engine to provide enough axial thrust, and with a sufficiently tight minimum impulse bit, to enable the close flyby rendezvous maneuvers. This is something I haven’t had the budget to simulate in detail, but it’s my preferred approach.
  • I should probably do another blog post at some point about the work Altius has done on cryogenic and storable refueling for rocket upper stages. Long-story short, our approach is focused on minimal modifications to the T-0 umbilical ports that the stages already typically have to have to enable reconnecting umbilicals on orbit, combined with poseable individual-fluid transfer lines, because you’re going to be servicing a wide range of customers where you might be able to get standardized T-0 quick disconnect interfaces, but you’re almost certainly not going to be able to standardize things at the umbilical plate level (since not all stage use the same propellant combinations). More on that some other day.
  • Alternately, if such a close rendezvous approach isn’t feasible, another option would be to use a servicing tug to grapple the smallsat launcher stack and tow it to the depot. Depending on where the OOS ecosystem is by the time such a depot exists, this may be a relatively simple operation that can be “bought by the drink” by a servicer that also services other clients.
  • Michael Loucks, John Carrico, and I wrote an AAS paper that I discussed in a pair of previous blog posts, on the orbital dynamics of using such a depot. Some key takeaways from that study that are worth repeating in this blog post include:
    • For most beyond LEO missions, you’re going to want to refuel both the launcher 2nd stage and a storable propellant kick stage. The 2nd stage does your boost to a highly elliptical orbit, and the kick stage does the rest (plane changes at apogee, circularization burns if going to MEO/GEO, injection burns if going to lunar or deep space destinations).
    • For payloads that themselves don’t need much refueling, such a system was shown to enable you to send >80% of your LEO payload for the smallsat launcher onto a TLI, TMI, or TVI trajectory, and you don’t even need to top the second stage up all the way typically. So for RocketLab, if you could refuel and reuse their 2nd stage and their Photon stage9, you could send on the order of 250kg into an interplanetary trajectory this way, instead of the ~15-25kg they can send currently. With Virgin Orbit you’d be talking up to ~400kg, and for Firefly you’d be talking about nearly a ton.
  • One last consideration is the economics of such missions. Since your depot is buying its propellant wholesale, in bulk from larger, more efficient rockets, the depot enables much lower $/kg costs for interplanetary missions than you would think. I need to redo the analysis with updated details, and a good set of eyes looking at assumptions, but when I ran the numbers previously, you could run a pretty profitable depot where the depot mission was 1.5-2x the cost of a normal LEO launch by the smallsat launcher. But since using a depot increases the amount of beyond LEO payload you can launch with a dedicated smallsat launcher by typically a factor of 10x over what you could do with just putting a kick stage on without LEO refueling, my previous calculations were suggesting interplanetary missions at a price point around $50k/kg for many of the smallsat launchers was feasible, and with total mission prices much less than half the cost of a reusable Falcon 9. As I said earlier, I need to rerun the numbers, but I think those would be in an interesting price range for customers.

Anyhow, while we could definitely go on and dig way, way deeper into the technical weeds on how to do the depot, how to make an upper stage compatible with such a depot, how you’d do the rendezvous/prox ops for getting to the depot, and the economics of such a depot, hopefully you can see why this concept is potentially very powerful for enabling affordable, dedicated beyond LEO smallsat missions.

[Edit 11/16/2020: I completely buried the lede, and totally forgot to mention the fact that my company is working with Eta Space, a Florida-based cryogenic propellant management startup on their LOXSAT-1 flight demo under NASA’s Tipping Point Technologies program. This 9-month flight demonstration, which is set to launch on a Rocket Lab Electron vehicle in 2023, will demonstrate a suite of cryogenic fluid storage, management, and transfer technologies, including using a version of Altius’s cryogenic refueling coupler to transfer LOX between two tanks on orbit. Eta Space’s planned follow-on depot, LOXSAT-2, would be a LOX-Kerosene depot, potentially of the very kind described in this article. They’re targeting a 2025 timeframe for fielding this depot, and I’ll be supporting the Eta Space team on conversations with interested partners/customers, and development of design and mission concepts for LOXSAT-2. After years of talking about propellant depots, I’m personally really excited to be supporting Eta Space and NASA on this project.]

Next-Up An Updated Propellant Depot Taxonomy Part V: Human Spaceflight Fixed Depots (Low-Orbit)

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