Small Launch Vehicles

Technology Roadmap Sections and Deliverables

• 1SLV - Small Launch Vehicles

Roadmap Overview

Small launch vehicles (SLVs, also called "Small launchers" or "Small-lift launch vehicles") are a category of orbital launchers capable of carrying a payload of maximum 2000kg* to LEO (Low Earth Orbit). Half a century ago, many families of launch vehicles have started as small launchers, as prototypes, and have led to today's large landscape of heavy launch vehicles (Ariane V, Falcon 9, Soyuz, Delta IV...). Today, the growing market of small satellites (below 500kg) - including, notably, LEO constellations projects and cubesats - pushes towards dedicated small launchers. This trend started in the 1990s and considerably accelerated in the 2010s with the development of a broad ecosystem of SLV startups. In comparison to conventional (heavy) launch vehicles, SLVs have: a higher scheduling flexibility, a higher launch frequency, a much lower total cost but a higher cost per kg of payload.

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  Classification of SLVs among launch vehicles on their payload capacity. Source: SpaceCapital.

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  Launch profile of a typical SLV mission with 2 stages and non-reusable rocket (Antares here). Source: Northrop Grumman.

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  Launch of the Electron SLV (Rocket Lab). Source: Rocket Lab.

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  System decomposition of a SLV (Electron here). Source: Rocket Lab.

*: Diverse definitions exist. Some define small launchers as limited to 1 ton instead of 2 tons, some also define a lower boundary of 500kg under which launchers are called 'micro-launchers'.

Design Structure Matrix (DSM) Allocation

The technology hierarchy demonstrates that such technologies as metal 3-D printing and modulable launchpads are supporting the development of small launchers. Initiatives and development plans for these technologies enhance small launchers by increasing their reusability, launch rate, scheduling flexibility, and reducing their cost per kilogram to launch payloads into orbit.

Roadmap Model using OPM

We provide below an Object-Process-Diagram (OPD) of the 1SLV roadmap. This diagram captures the main object of the roadmap, its decomposition into subsystems (engines, avionics, payload...), its characterization by Figures of Merit (FOMs) as well as the main processes and actors involved.

An Object-Process-Language (OPL) description of the technology is auto-generated and given below:

Figures of Merit

Figures of Merit (FoM) used to evaluate small launchers are very similar to the FoMs of conventional launch vehicles, but they have redefined the priorities among these. Typical FoMs for small launchers are:

Figure of Merit (FOM)	Unit	Description
Launch Frequency	[launches/month]	The number of launches a launch vehicle can perform in a month
Reliability	[% of successful launches]	The percentage of launches out of total launches that are successful as determined by ability to meet end requirements of customers
Payload mass capacity	[kg of payload to 500km LEO]	The amount of payload in kilograms that can be launched to 500km Low Earth Orbit (LEO) with the launch vehicle. LEO is a large range and so this FOM standardizes the various launch vehicles by specifying 500km LEO
Total cost	[$]	The total cost of the launch to include fixed and variable costs
Cost per kg	[$/kg of payload to LEO]	The total cost of the launch divided by the amount of payload to 500km LEO
Reusability	[Number of reuse cycles]	The number of times a launch vehicle can be reused before a new one must be built
Scheduling flexibility	[weeks or months or years]	How quickly the launch vehicle can go from initial talks with customer to launch to LEO. (Sometimes called Responsiveness, it is the duration between the launch window and the notification of its flight parameters - orbit, latitude, date, etc.)

In general, small launcher companies aim for very high launch rates (weekly instead of monthly), high scheduling flexibility (months instead of years), and low launch costs thanks to significant economies of scale enabled by mass production. Some also leverage uncommon launch strategies (balloons, planes, catapults), but here we only include into our scope actual orbital launchers with launching pads on earth or on sea.

The following plots have been built using a database our team built and plan upgrade regularly throughout time. Main sources of information are SpaceFund.com, Newspace.im and small launcher companies' websites and user guides.

Using a simple linear regression model, we can find a decreasing cost of: $$-2930.4\$/kg/year$$ This means that costs for launch are project to decrease by $2930.40 per year. This is a rough estimate and data is still being collected to make this model more accurate as small launchers are relatively new and data is scarce.

The physics of launchers is governed by the Rocket Equation:

$$\Delta V = v_e \log(\frac{m_0}{m_f})$$

<math> \Delta V </math> is the change of velocity available to the missile

<math> m_0 </math> is the initial wet mass

<math> m_f </math> is the (final) dry mass

<math> v_e </math> is the effective exhaust velocity