ABL Payload User’s GuideABL SPACE SYSTEMS COMPANYABL Payload User’s Guide
CONTENTS
Contents ........................................................................................................................................................................................................... 1
1

ABL Overview ..................................................................................................................................................................................... 3

2

Mission Capabilities ........................................................................................................................................................................ 33

2.1

Orbital Capabilities................................................................................................................................................................. 3

2.2

Performance.............................................................................................................................................................................. 3

2.3

Mission Profile ..........................................................................................................................................................................4

2.4

Insertion Accuracy .................................................................................................................................................................5

2.5

Deployment Accuracy ..........................................................................................................................................................5

RS1 Launch Vehicle ........................................................................................................................................................................ 6
3.1

Coordinate System ................................................................................................................................................................8

3.2

Engines ........................................................................................................................................................................................8

3.3

Avionics ...................................................................................................................................................................................... 9

3.4

Guidance, Navigation, and Controls (GNC) .............................................................................................................. 9

3.4.1
3.5
4

Stage and Fairing Separation Systems .................................................................................................................... 10

Payload Accommodations........................................................................................................................................................ 10
4.1

Payload Envelope ................................................................................................................................................................ 10

4.2

Mechanical Interfaces ........................................................................................................................................................ 11

4.2.1

Primary Payload Interfaces ................................................................................................................................... 11

4.2.2

Secondary Payload Interfaces ............................................................................................................................12

4.3

5Mission Design ............................................................................................................................................................. 9Electrical Interfaces .............................................................................................................................................................12

4.3.1

Payload to RS1 Electrical Interfaces .................................................................................................................12

4.3.2

Payload Separation Indication .............................................................................................................................12

4.3.3

Payload to Ground Electrical Interfaces .........................................................................................................13

Environments ....................................................................................................................................................................................13
5.1

Ground Environments .........................................................................................................................................................13

5.2

Flight Environments ............................................................................................................................................................ 14

5.2.1

Acceleration Loads................................................................................................................................................... 14

5.2.2

Random Vibration ..................................................................................................................................................... 15

5.2.3

Acoustic Loads........................................................................................................................................................... 16

5.2.4

Shock Loads ................................................................................................................................................................. 17

5.2.5Radio Frequency ....................................................................................................................................................... 18

Page 1 of 31

5.2.6

Fairing Internal Pressure ........................................................................................................................................ 19

5.2.7

Payload Thermal ........................................................................................................................................................ 19

5.2.8

Free Molecular Heating .......................................................................................................................................... 19

5.3
6

Mission Management.................................................................................................................................................................. 20
6.1Standard Services ............................................................................................................................................................... 20

6.2

Customer Requirements ...................................................................................................................................................21

6.3

Insurance ................................................................................................................................................................................. 22

6.4

Payload Safety ...................................................................................................................................................................... 2278Facilities ............................................................................................................................................................................................. 22
7.1

ABL Headquarters ............................................................................................................................................................... 23

7.2

Launch Sites ........................................................................................................................................................................... 23

7.2.1

Vandenberg Space Force Base (VSFB) LC-576 ............................................................................................. 24

7.2.2

Cape Canaveral Space Force Station (CCSFS) Station and Kennedy Space Center (KSC) 24

7.2.3

SaxaVord Space Centre, UK................................................................................................................................ 24

7.2.4

Kodiak, Alaska............................................................................................................................................................. 24

7.3

Ground Systems (GS0) ..................................................................................................................................................... 24

7.4

Payload Processing Facilities ........................................................................................................................................ 25

7.5

Test Facilities ......................................................................................................................................................................... 25

Launch Operations........................................................................................................................................................................ 26
8.1

Payload Processing ............................................................................................................................................................ 27

8.1.1

Payload Encapsulation ................................................................................................................................................ 27

8.1.2

Security .......................................................................................................................................................................... 27

8.1.3

Countdown Operations.......................................................................................................................................... 27

8.2

9Payload Environmental Compliance........................................................................................................................... 19

Flight Operations ................................................................................................................................................................. 28

8.2.1

Liftoff and Ascent...................................................................................................................................................... 28

8.2.2

Payload Separation and Reporting .................................................................................................................. 28

8.2.3

Collision Avoidance.................................................................................................................................................. 28

8.2.4

Post Launch Reports ............................................................................................................................................... 28

Document Reference................................................................................................................................................................... 29
9.1

List of Tables .......................................................................................................................................................................... 29

9.2

List of Figures ........................................................................................................................................................................ 29

9.3

List of Acronyms .................................................................................................................................................................. 29

Page 2 of 31

ABL OVERVIEWABL Space Systems (ABL) was founded in 2017, and the rapid hardware development capability andfocused business approach have quickly positioned the company as a leader in the small launch market.
ABL’s launch vehicle RS1 is a two-stage, ground-launched rocket. The vehicle is deliberately simple anddesigned for high-rate manufacturing and streamlined launch operations.
Based in El Segundo, California, ABL already occupies several facilities with end-to-end manufacturing
capabilities in-house, including 3D printing, precision machining, forming, and welding. ABL’s highlyverticalized engineering approach allows for a heightened control over both schedule and quality.
ABL’s flagship vehicle is RS1, with a maximum capacity of 1,350kg to LEO; small enough to simplify
development, manufacturing, and operations, but large enough to deliver a per-satellite launch cost at afraction of a smaller vehicle. In addition, ABL offers a high degree of flexibility via GS0, a 100% containerized
launch solution for responsive deployment with minimal existing ground infrastructure.
ABL’s mission is to develop simple, reliable, and low-cost launch vehicles for the small satellite industry.

MISSION CAPABILITIES
Orbital Capabilities
With multiple launch sites, ABL can deliver to a wide range of orbits in order to meet customer needs. See
Figure 0-1 for an overview of orbital capabilities. For orbits outside of the ranges below, please contact ABL
directly.
Table 0-1: Orbital Capabilities

Launch Site
Cape Canaveral Space Force Station, FL
Vandenberg Space Force Base, CA
Pacific Spaceport Center, AK
SaxaVord Spaceport, UK

Available Orbits
Mid-inclination, GTO
Mid- to High-inclination and polar orbits
Mid- to High-inclination and polar orbits
High-inclination and polar orbits

Performance
RS1 utilizes a relightable second stage engine, which can deliver payloads to many unique orbits. As areference, most missions will require two second stage burns. With this two-burn mission design, RS1 iscapable of deploying 970kg to a 500km Sun-Synchronous Orbit (SSO). RS1 performance capability for arange of mission inclinations is presented in Figure 0-1. Please contact ABL to discuss any specificperformance needs that are outside of the orbits presented.
ABL recognizes the expanding market of small satellites beyond low earth orbit (LEO) to medium earth orbit(MEO) and even geostationary earth orbit (GEO). RS1 is designed to access the higher altitude orbits of
MEO and geostationary transfer orbit (GTO). This capability includes rigorous mission design protocol, as
well as provisions for longer coasts between Stage 2 burns (for example, higher capacity batteries).
While MEO and GTO performance are more mission-dependent and require mission-specific analysis, RS1
can carry approximately 700 kg to an elliptical 8,000 km MEO transfer orbit and 320 kg to GTO. Customers
interested in these orbits are encouraged to contact ABL for feasibility analysis.

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LEO Payload Capability

1350.0

28.5°
42.0°

Payload Capability (kg)1250.060.0°1150.01050.0

SSO

950.0

850.0

750.0
100

200

300

400

500

600

700

800

900

1000

1100

1200

1300

Orbit Height (km)Figure 0-1: RS1 LEO Payload Capability

Mission Profile
The RS1 is a two-stage to orbit launch vehicle with stage separation occurring at approximately 160
seconds into flight. Second Stage Engine Cut Off (SECO) is specific to each mission, but in a standard
reference mission SECO-1 will occur at approximately ~508 seconds at a 200km altitude. Payload
separation occurs once Stage 2 reaches the desired orbital parameters for the payload. Please see Figure
0-2 for a summary of major events and their timing for a standard reference mission.

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Stage 2 Startup
Time: 163s
Altitude: 80 km
Velocity: 2.6 km/s

Fairing
Separation
Time: 200s
Altitude: 125 km
Velocity: 2.65
km/s

MECO/Stage
Separation
Time: 160s
Altitude: 75 km
Velocity: 2.6 km/s

SECO
Time: 508s
Altitude: 200 km
Velocity: 7.8 km/s

Payload Separation
Time: 518s
Altitude: 200 km
Velocity: 7.8 km/s

Fairing Reentry

Stage 1 Reentry
Liftoff
Time: 0:00
Altitude: 0 km
Velocity: 0 km/s

Figure 0-2: Reference mission timing of major events

Insertion Accuracy
Orbital injection accuracies are presented in Table 0-2. The standard (± 7.5°) tolerance for the Right
Ascension of the Ascending Node (RAAN) is based on a 1-hour launch window, which is ABL’s baseline
operation. Significantly tighter RAAN accuracy can be achieved with an instantaneous launch window,
which ABL offers with additional mission planning.
Table 0-2. Orbital Parameter Accuracy

Perigee [km]Apogee [km]Inclination [deg]Argument of Perigee [deg]RAAN [deg]± 15± 15 LEO, ± 275 GTO± 0.15± NA LEO, ± 0.3 GTO± 0.2 to ± 7.5

Deployment Accuracy
RS1 uses a cold gas thruster system to control attitude and body rates. Table 0-3 presents standard
deployment attitude and body rates for a three-axis stabilized deployment. RS1 can support other
deployment methods, and mission-specific payload injection accuracy bands are calculated duringnominal pre-flight mission analysis by ABL.

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Table 0-3. Attitude and Body Rates for a Three-Axis Stabilized Deployment

Parameter
Roll
Pitch
Yaw

Angular Error [deg]Rate Error [deg/s]

±2.0
±2.0
±2.0

±0.1
±0.1
±0.1

RS1 LAUNCH VEHICLE
RS1 is a two-stage, ground-launched vehicle (Figure 0-1) that uses nine E2 Sea Level engines on the firststage and one E2 Vacuum engine on the second. RS1 is six feet in diameter and 88-feet long when fully
integrated. Both stages use liquid oxygen (LOx) as oxidizer and kerosene as propellant. The vehicle’s primarystructure is entirely metallic, employing high-strength, reliable aluminum alloys. RS1 utilizes a common dometank architecture to minimize structural mass. Tank barrels are grid-stiffened with an isogrid design. The
front end of the vehicle includes a custom-designed payload adapter fitting and a metallic bi-conic fairingwith acoustic protection.
RS1 components and pressurization systems are optimized for simplicity, enabling rapid production andsimple operation. Stage, fairing, and payload separation devices are non-pyrotechnic to enable simple
handling procedures, minimize payload shock environments, and increase mission assurance.
RS1 avionics systems are highly modular and rigorously tested to ensure reliability. RS1 is provisioned forboth classic and autonomous flight termination systems to provide flight safety as range safety protocols
require. Avionics systems employ hardware redundancy and fault-tolerant software design to ensure highlevels of reliability.
To support transportation and handling operations, all RS1 assemblies can be packaged into standard
shipping containers.

Page 6 of 31

Figure 0-1: RS1 Overview

Table 0-1. RS1 Overview

Item

Unit

Stage 1

Stage 2

Total Length
Diameter
Propellants
Feed system
Engine Cycle
Engine ThrustEngine Quantity
Total Thrust
Pitch Control
Yaw Control
Roll Control

ft
ft
lbf
lbf
-

50
6
LOx and Kerosene
Turbopump
Gas Generator
12,100 (sea-level)
9133,118 (sea-level)
Thrust Vector
Thrust Vector
Thrust Vector

5.4
6
LOx and Kerosene
Turbopump
Gas Generator
13,000 (vacuum)1
13,000 (vacuum)
Thrust Vector
Thrust Vector
Cold Gas

Page 7 of 31

Coordinate System
The launch vehicle (LV) coordinate system is defined as:
LV Body Axis:§§§+X: LV roll axis, directed through the LV fairing nose
+Y: LV pitch axis, completes a right-handed coordinate system+Z: LV yaw axis, directed opposite of the LV raceway

The LV coordinate system origin is 90 inches aft of the exit plane formed by the stage 1 engine nozzles(Figure 0-2).

Figure 0-2. LV Coordinate System

Engines
ABL developed the E2 engine (Figure 0-3) from a clean sheet with a focus on
simplicity to meet the requirements of the RS1 launch vehicle. E2 is a gas
generator cycle engine and produces 13,000 lbf (vac) of thrust. RS1 utilizes E2
on both stages to capture manufacturing economies of scale. Stage 1 utilizes
nine sea level optimized E2 engines, while Stage 2 uses one vacuum optimized
E2 engine.
Additive manufacturing is used in select engine components to structurally
optimize components and reduce manufacturing steps to rapidly produce
components. This targeted use of additive manufacturing allows complex
internal fluid passageways to be incorporated without the need for complex
joining processes. Strict process control is implemented on all printed parts, Figure 0-3: E2 Sea Level Engine
Page 8 of 31

which are subject to rigorous material property validation and quality control requirements. This ensuresreliability of the parts manufactured with advanced methods.
All E2 engine components are designed in-house, including the turbopump, main propellant valves, thrustchamber assembly, and gas generator, which gives ABL complete control over the engine architecture andupgrade roadmap. ABL machines and prints most E2 engine parts in-house, minimizing the designmanufacturing feedback loop. This provides tight control over production schedule and the ability to readilyscale engine manufacturing.

Avionics
The RS1 avionics system combines proven off-the-shelf components and simple ABL designs. Beyond
minimizing technical risk, the team has focused on tailoring redundancy for different aspects of the system
to minimize failure modes and comply with the FAA and Range licensing frameworks.

Figure 0-4: Avionics manufacturing bay at ABL headquarters

Guidance, Navigation, and Controls (GNC)
ABL’s guidance, navigation, and control (GNC) architecture is typical of a modern LV system. RS1’snavigation state is a blended combination of both Global Navigation Satellite System (GNSS) and inertial
measurement unit (IMU) sensor data. The actuation systems used are Thrust Vector Control (TVC) and acold gas Reaction Control System.
Flight algorithms are designed to allow simple adjustments to the mission profile and launch site location
with minimal configuration parameters. RS1 has been designed to be robust to high altitude winds toincrease launch availability and simplify day-of-launch analysis.

Mission Design
Preliminary flight trajectory optimization is executed in a 3 degree-of-freedom (3DOF) simulation
environment to scope a mission. With moderate fidelity, these simulations provide a rapid, first ordersimulation of vehicle performance. 3DOF analysis is particularly useful for preliminary mission design where
iteration is expected and can be performed rapidly on customer request.
For detailed mission planning, ABL uses a high-fidelity 6 degree-of-freedom (6DOF) simulation
implemented on a hardware-in-the-loop (HITL) test bed to verify mission design and guarantee mission
Page 9 of 31

assurance. These tools provide high fidelity performance modeling and run on a real-time computer. HITL
extends testing beyond the software implementation to include flight-like avionics hardware. The fullavionics suite is integrated on the testbed, allowing guidance algorithms to run on flight hardware. Multiple
test cases simulate corner-case flight conditions, on top of which Monte Carlo methods are layered toperform robust testing. Strong system modeling allows ABL to simulate missions and execute data review
in a flight-like manner.
Every RS1 launch vehicle also undergoes vehicle HITL testing prior to launch to verify all mission
configurations and parameters.

Stage and Fairing Separation Systems
The RS1 stage separation event occurs shortly after the termination of the first stage thrust. RS1 stage
separation is accomplished by six equally spaced mechanisms around the circumference of the vehicle.
Each mechanism is comprised of a pneumatically-actuated mechanical latch and a pneumatic pusher. Allstage separation mechanisms are designed, built, and tested in-house.
RS1 uses split spool devices and springs for fairing separation. Before fairing separation occurs, the fairing
halves are held together and to Stage 2 via several electrically-actuated hold down and release mechanisms(HDRMs). The HDRMs are non-pyrotechnic release mechanisms which are commercially available and have
many years of flight heritage across several active launch vehicles. Fairing separation is then initiated byactuating the HDRMs, and four in-house spring-based pushers passively act to separate the fairing halves,
which rotate and fall away from the vehicle via hinges near the base of the fairing.

PAYLOAD ACCOMMODATIONSPayload Envelope
As a standard, RS1 uses a metallic, milled 80-inch (2.032m) diameter bi-conic fairing to shield the payload
from aerodynamic buffeting and heating during ascent. The fairing is provisioned with acoustic protection
provisions with ample clearance for dynamic movement of the fairing and payloads during the ascent. The
fairing is a two-part assembly and separates along a longitudinal seam using low shock pneumatic and fully
testable actuators.

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In addition, ABL offers an expanded fairing option of 108” for customers that need a larger envelope.

Figure 0-1: RS1 Dynamic Envelopes for 80” Hammerhead (left) and 108” XL Fairing (right) Options

Mechanical Interfaces
Primary Payload Interfaces
The RS1 Payload Attach Fitting (PAF) is designed to be adaptable with standard interface ring diameters
up to a 38.81-inch bolt circle. This interface is directly compatible with most separation release systems
from Planetary Systems Corp, RUAG, Moog, and other commercial or ABL-custom built secondary
adapters. ABL can procure the payload separation system that interfaces with the RS1 PAF as a nonstandard service, upon request.
The 38.81-inch PAF interface is referenced below in Figure 0-2.

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Figure 0-2: PAF 38.81 Inch Mechanical Interface

Secondary Payload Interfaces
The RS1 PAF is compatible to host all commercially available CubeSat dispensers. A customized ABL-built
or commercially available secondary structure will be used to accommodate the installation of the CubeSat
dispensers.

Electrical Interfaces
Payload to RS1 Electrical Interfaces
The RS1 Flight Computer provides the signals to separate the payloads. The deployment signals can beprovided via un-regulated 28V or regulated 10V circuits with various pulse widths and current limiting
resistors installed as required. These circuits are routed from the Flight Computer to the payload via directconnection or through an interface panel on the PAF. The RS1 Flight Computer commands both primaryand redundant deployment signals simultaneously or can offset signal timing as required.
FlightComputer
Ground
EGSE

PayloadRaceway

PAF

Figure 0-3: RS1 Electrical Interfaces

Payload Separation Indication
The RS1 flight computer will monitor the separation switches or loop-back (break-wire) signals upon
separation from the PAF or dispenser. These circuits are routed from the payload deployment system toPage 12 of 31

the flight computer on Stage 2. This configuration is mission-unique depending on the separation systems
utilized and the number of payloads and will be defined in the mission Interface Control Document (ICD).

Payload to Ground Electrical Interfaces
The RS1 provides a customizable electrical interface for primary payloads requiring power, battery charging,telemetry, and other command/control functions via a maximum of 75 twisted/shielded pairs (22 gauge) for
signal data, 12 twisted pairs (20 gauge) for lower current transmission and 5 twisted pairs (16 gauge) for
higher current transmission. This umbilical interface uses an Amphenol R27 quick disconnect connector thatis built-in to the RS1 launch mount and a 184-wire umbilical cable that runs to the primary payload electricalground support equipment accommodation that is housed in a smaller environmentally and physicallycontrolled container called the Payload T-0 EGSE Container (PTEC). The PTEC has a junction box connector
for payload EGSE racks. Additional conveyances can be provided to route communication signals via
copper, fiber, etc. to off-pad facilities. A terminal block is provided that can be used to re-configure theumbilical circuit wires as required for the payload servicing.

Figure 0-4: Payload – Ground Electrical Interface

ENVIRONMENTS
Characterizing payload environments is critical for payload design and mission assurance. Most
environments are mission-dependent and require test and flight data to accurately determine frequencies
and magnitudes. ABL gathers acoustic, dynamic, and shock data during all component, ground, and flighttests. This data can be provided on request during mission planning. For design and feasibility analysis
purposes, design reference environments are presented below. Mission environments will not exceed thereferences presented, except as mutually agreed by all parties during mission planning.

Ground Environments
Payload thermal and humidity environments are tightly monitored and controlled while ABL has custody ofthe payload. While in the payload processing facility, the processing environment temperature will be

Page 13 of 31

maintained between 60° to 80° Fahrenheit during operations where the payload is present, and theprocessing environment humidity will be maintained between 35% to 65% relative humidity.
Payload processing and fairing encapsulation is performed in an ISO 8 (Class 100,000) cleanroom, althoughhigher cleanliness levels are possible ISO 7 (Class 10,000) upon request. Once encapsulated, the payload
is supplied with a clean, dry air supply or a low-flow GN2 purge until final mate to the RS1 vehicle. Oncemated to the LV, a GN2 purge is initiated and maintained until launch. Temperatures are always maintained
above the dew point.
Once the Encapsulated Assembly (EA) is mated to the LV, the fairing purge is maintained via the LV umbilicaland the environment is monitored remotely via launch control displays.
Table 0-1. Payload Thermal and Humidity Environments

Environment
State

Temperature

Humidity

Cleanliness

Payload Processing

70° ± 10°50% ± 15%

ISO 8 (Class 100,000)

Roll Out Transportation

70° ± 10°50% ± 15%

ISO 8 (Class 100,000)

Vertical on Pad

70° ± 10°50% ± 15%

ISO 8 (Class 100,000)

Flight Environments
Acceleration Loads
During ground operations and in flight, the payload is subjected to axial and lateral accelerations. The axial
direction is in line with the RS1 longitudinal axis. The lateral direction is orthogonal to the longitudinal axis.
These loads are enveloped by the values presented in Table 0-2. Loads with a positive sign arecompressive.
Table 0-2. Flight Load Factors

Lateral [g]Axial [g]Ground Handling±1±2

Flight±2+6/-1.5

Figure 0-1 illustrates the approximate acceleration profile during a single-burn mission with 1,350kg
deployed to a 200km circular orbit. While each mission has a unique acceleration profile, this trend isrepresentative of the maximum acceleration payloads will experience.

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7

Axial Acceleration (g)

6
5
4
3
2
1
0
0

100

200

300

400

500

Mission Time (s)Figure 0-1. Reference Mission Acceleration Profile

Random Vibration
Random vibration is generally a driving load condition on the LV. The RS1 random vibration environments
will not exceed NASA’s General Environmental Verification Standard (GEVS). ABL maintains and validates
these levels through analysis, testing, flight data, and component/isolator design.
Table 0-3. NASA GEVS Protoqualification Levels

Frequency [Hz]PSD [g2/Hz]

20
50
800
2000

0.026
0.16
0.16
0.026

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Power Spectral Density (G^2/Hz)

1.000

0.100

0.010

0.001
10.00

100.001000.00

10000.00

Frequency (Hz)Figure 0-2: NASA GEVS Random Vibration Protoqualification Levels

Acoustic Loads
RS1 utilizes acoustic protection within the bi-conic fairing to maintain the Overall Sound Pressure Level(OASPL) below 135dB for the duration of the mission through liftoff and ascent. The P95/50 acoustic
environment levels are shown in Table 0-4, with an OASPL of 129.5dB for the empty PLF and OASPL of
132dB for a 50% full PLF.
Table 0-4: Maximum Flight-Level Payload Acoustic Environment

Freq (Hz)SPL (dB)

50% full
SPL (dB)

16
20
25
31.5
40
50
63
80
100
125
160

116.1
116.8
117.5
118.1
119.0
119.5
119.7
119.5
119.1
118.2
117.9

119
119.8
120.4
121.1
122
122.4
122.6
122.4
121.9
121
120.7
Page 16 of 31

200
250
315
400
500
630
800
1000
1250
1600
2000
OASPL

116.3
113.2
111.1
110.0
111.1
112.2
104.4
105.6
106.9
99.4
97.0
129.5

119
115.8
113.6
112.4
113.4
114.3
106.5
107.5
108.6
100.9
98.4
132.4

Figure 0-3: P95/S0 SPL for Fairing Cavity

Shock Loads
Four events during RS1 flight create shock loads: liftoff hold down release, stage separation, fairing
separation, and payload separation.
RS1 utilizes non-pyrotechnic separation devices for all vehicle separation events, which limits the shockloads imparted to the payload. Figure 0-4 presents an approximate shock response spectrum for a typicalprimary payload separation device.

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Shock Response Spectrum (g)

10000

1000

100

10
100

1000

10000

Frequency (Hz)Figure 0-4: Approximate Shock Response for Payload Separation

Radio Frequency
The RS1 launch vehicle transmits and receives data in the frequency bands specified in Table 0-5. Specificfrequencies vary by mission and in some instances are range dependent.
Table 0-5: RS1 Radio Frequency System characteristics

Data Type

Mode

Antennas

Band

Frequency [MHz]GPS

Receive

2

L-Band

L1: 1575.42
L2: 1227.60

Telemetry

Transmit

2

S-Band2200.5 - 2394.5

FTS Command

Transmit/Receive2

UHF

400.0 – 460.0

All primary and secondary payloads must pass testing per SMC-STD-461 for radiated emissions andsusceptibility. Generally, it is advised that payloads are powered off during launch to reduce risk of RFinterference.

Page 18 of 31

Fairing Internal Pressure
During ascent, an overpressure in the fairing of about 0.15 psi above external pressure is maintained. The
maximum depressurization rate is 0.5 psi/s, which occurs during transonic flight. Excluding transonic flight,
the fairing depressurization rate is generally 0.25 psi/s throughout the mission.

Payload Thermal
The payload fairing heats minimally during ascent, and the temperature that the payload is exposed to willremain below 90°C. Mission-specific thermal analysis can be performed using payload thermal models
upon request.
On orbit, certain trajectories may benefit from an RS1 Stage 2 roll during coast to ensure even solar heat
flux across the payload. Attitude pointing and roll control of up to 2 deg/s can be provided if thermal analysis
demonstrates that this is required.

Free Molecular Heating
RS1 fairing deployment occurs when free molecular aero-thermal heating is less than 1,135 W/m^2. This isa time-based determination from 6DOF simulations and Monte Carlo methodology.

Payload Environmental Compliance
The payload requirements for primary and secondary payloads are outlined Table 0-6.
Table 0-6. Payload Requirements

Resonance and First
Natural Frequency

The 1st lateral resonant frequency must
exceed 10 Hz. The 1st axial resonant
frequency must exceed 25 Hz.

Random Vibration

The payload must withstand random
vibration at the levels presented in Table 0-3.

Acceleration Loading

The payload must withstand accelerationloads presented in Table 0-2.
Preliminary mass must be reported to within+/- 5lbm

Mass

RF Transmission

For Cubesats, nominal masses expected,
higher masses acceptable with ABL
approval (1U: 1.33kg, 3U: 4kg, 6U: 12kg)
Payloads are nominally powered off and nottransmitting during launch. If a customer
requests the payload to be powered on
during launch, an RS1 compatibility test must
be executed.

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MISSION MANAGEMENTABL supports a wide range of small satellite mission profiles, from multi-launch constellation deployments
to rapid responsive launch of single payloads. Because each customer’s needs are different, ABL assigns a
dedicated mission manager to each launch. Through this liaison, ABL’s customers have a single point ofcontact with ABL’s technical team to ensure all requirements are met.
Standard launches can be single payloads or a combination of multiple payloads. ABL also supports avariety of non-traditional launch capabilities including rapid, responsive launch and deployable, fieldoperable launch. For details on these capabilities, please contact ABL directly.
ABL’s Mission Integration process envelopes all payload services as they pertain to LV and mission
planning, design, analysis, development, production, integration, and testing. ABL’s mission management
team is trained and well-versed in working with both dedicated and rideshare missions and will collaborate
with the customer to ensure that compatibility between the payloads and the LV (and between otherpayloads, in the case of rideshare missions) is a smooth and timely process.

Standard Services
As part of a launch service agreement, ABL performs a standard set of customer services. The details ofthese services are defined in the mission-specific Statement of Work.
§
§
§
§
§
§
§

Mission Analysis. ABL performs Monte Carlo trajectory analysis to verify performance, as well as
separation and recontact analysis. The results of a standard CLA and heating analysis are used toverify spacecraft loads.
Interface Control Documentation. ABL creates and maintains an ICD that defines all connections,interfaces and coordinated operations between the customer and ABL. As part of this effort, ABL
also maintains record of all verifications for the ICD.
FAA Launch License. ABL coordinates and secures an FAA Launch License with customer andmission specific inputs.
Payload Processing. ABL provides ISO 8 payload processing facilities with temperature andhumidity control.
Payload Management. On the launch pad, ABL provides payloads with environmental control until
T-0.
Payload Separation. ABL provides separation control and monitoring for all primary and secondary
payloads.
Orbital Insertion. After the mission concludes, ABL provides the customer with separation
confirmation, a state-vector, and all orbital insertion parameters.

In addition to ABL’s standard services, additional optional services can be arranged and included in the
Launch Service Agreement Statement of Work.
§
§
§
§
§
§

In-Flight Data. Primary payload data signals can be routed through the vehicle avionics to provide
real-time payload telemetry during flight.
Additional Analysis. ABL can perform additional cycles for CLA and thermal analysis.
Payload Transport. ABL can arrange transport of the payload to the launch site.
Separation System. ABL can provide a range of compatible separation systems for payloads uponrequest.
Payload Adapter Fitting Customization. Customized mechanical fittings can be provided by ABL
should the payload not fit the standard payload adapters offered.
Advanced Orbit Planning ABL can perform on-orbit thermal management maneuvers or provide
custom orbital planning including orbit spacing between payloads or a change of orbital altitudes
or planes for multiple payloads.

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§§§

Launch Pad T-0 Umbilical Connection. ABL can provide a separate, secure Customer EGSE room
located at the launch pad as well as day-of-launch umbilical connections to the payload. Payload
telemetry can be monitored from the control room.
Payload Fueling. ABL can assist with procurement as well as support fueling activities at the
payload processing facilities, including hazardous operations.
Rapid Launch. For customers with time-sensitive missions, ABL offers responsive launch options.

Customer Requirements
Table 0-1 gives an example timeline of customer deliverables that ABL will require from authority to proceed(ATP) to launch. The requirements timeline is subject to change in accordance with mission and customer
requirements.
Table 0-1: Example timeline of deliverables from both parties

Time
ATP

ATP+2 weeks

ATP+2 months
ATP+3 months

Customer to ABLContract Signature
Mission/Orbit Specifications
Payload Questionnaire and Specifications (such as
CAD)
Payload CLA Model (if applicable)
Mission Specific ICD edits
Preliminary Payload Layout Design

L-10 months

Preliminary Payload Processing/Range Safety Inputs

L-8 months

Payload Thermal Model (if applicable)

L-7 months

Electrical and Mechanical fit checks

L-6 months

Mission ICD signed
Payload Test Plan(s)L-4 months

Launch License Inputs
Daily Payload Processing Schedule
Final Mass Properties

L-45 days

Payload License Confirmations
Payload Readiness Confirmation
As-measured Mass Properties
FAA Cross-waivers signed

L-30 days

Payload arrives at launch site or processing facility

L-2 days

Launch Readiness Review

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Insurance
All aspects of ABL launches are insured by premier underwriters in the space insurance market. ABL is
responsible for third-party liability coverage, while customers are responsible for insuring their payload.

Payload Safety
ABL follows AFSPCMAN 91-710 Range Safety User Requirements, regulations in FAA 14 CFR 417, as wellas certain other specifications and range requirements. Customer flight and ground systems must adhere
to the requirements of these documents. Critical safety requirements include:§

Payload Batteries. Battery overcharge protection is required to mitigate explosion risk.

§

Pressure Vessels. Payload pressure vessels must adhere to ATR-2005(5128)-1 Operational
Guidelines for Spaceflight Pressure Vessels. Customers should coordinate with ABL forpressurization timelines. Pressure vessels should have relief mechanisms to protect against burst.

§

Propulsion Systems. Payload propulsion systems must meet the requirements of AFSPCMAN 91710 and their general characteristics must be communicated to ABL in the Payload Questionnaire.

§

Ground Support Equipment. Ground support equipment should adhere to safety standards of 14
CFR 417. Any equipment that is loaded should have the limit load clearly marked. Lift points for all
equipment should be marked. Electrical protection against battery overcharge is required. Relief
valves are required on all pressurized fluid systems.

§

Pyrotechnic and Explosive Devices. Generally, ABL does not handle payloads with pyrotechnic or
explosive devices. If a payload has a pyrotechnic device, ABL requires appropriate advancecustomer coordination.

ABL can provide guidance on documentation required to meet Range requirements and will coordinate with
the Customer on compliance well in advance of launch.

FACILITIESABL's headquarters are located in El Segundo, CA, in close proximity to the test facilities at Mojave Air andSpace Port and Edwards Air Force Base further described in Section 7.5 below. ABL’s headquarters andtest site locations allow for easy access to the test sites for ABL engineering and operations staff, and also
serve to enable quick iteration and turnaround times during test campaigns.
In addition, ABL is activating multiple launch sites as depicted in Figure 0-1 below.

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Figure 0-1: ABL launch sites, offices, and test facilities

ABL Headquarters
The ABL campus in El Segundo includes four buildings, totaling 80,000 square feet of manufacturing andtest space. The El Segundo campus contains all design engineering, fluid system and avionics integration,
environmental testing, tank manufacturing, and LV integration. In addition, the campus contains alarge, state-of-the-art machine shop, capable of producing the company’s most complex parts, and areasfor ground system fabrication, storage, and refurbishment.

Launch Sites
RS1 and GS0 are designed to be packaged into standard shipping containers and operated from a flat
concrete pad of 150’ x 50’. This capability dramatically reduces the time and cost of activating new launchsites. ABL can operate from both dedicated and shared launch pads, doubling launch capacity at eachrange, with fairing capsulation occurring from a local payload processing facility.
Table 0-1 outlines the coordinates and accessible inclinations from both domestic and international launchsites.
Table 0-1. United States Launch Sites Details

Site
Cape Canaveral, FL
Kodiak, AK
Vandenberg Space
Force Base, CA
Saxavord Space
Centre, UK

Lat. [deg]Lon. [deg]Min Inc. [deg]Max Inc. [deg]N 28° 27' 30"
N 57° 26' 09"

W 81° 31' 42"
W 152° 20'16"

28.5
59.6

57
110.2

N 34° 34' 34"

W 120°37’ 56"

57

104

N 60° 49 '04"

W 0°45'40.7"

90

SSO

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Vandenberg Space Force Base (VSFB) LC-576E
ABL has secured LC-576E on the northern area of VSFB as a dedicated, long-term launch facility. LC-576E’s
unique location offers ideal access for integration and distance from other launch sites and strategic assets
on base. This site enables access to SSO and polar orbits.

Cape Canaveral Space Force Station (CCSFS) Station and Kennedy Space Center (KSC)ABL has structured an agreement with Space Florida, a Florida state government organization, to conduct
RS1 launch operations from LC-46 at CCSFS. This site is similar in configuration to VAFB SLC-576E. This
site enables ABL to launch payloads to mid-inclinations, as well as Geostationary Transfer Orbit (GTO).

SaxaVord Space Centre, UK
ABL was selected in partnership with Lockheed Martin Corporation as the launch service provider for theUnited Kingdom Pathfinder Launch Program to be launched from the SaxaVord Spaceport located in Unst,
Shetland. Operating from SaxaVord, ABL can support missions to Sun-Synchronous, Polar and High
Inclination orbits.

Kodiak, Alaska
ABL has entered into a formal agreement with Alaska Aerospace Corporation for launch of RS1 from PacificSpaceport Complex (PSC) in Kodiak, Alaska. Pacific Spaceport Complex currently has six active launchpads, two suitable cleanrooms, and is capable of handling hazardous fueling operations.

Ground Systems (GS0)
ABL’s GS0 ground system is fully independent and self-sufficient, providing orbital launch capability fromany flat 150’ x 50’ concrete pad globally. Any air base or similar facility can be used as an orbital launch site.
For commercial applications, GS0 represents a differentiator in ABL’s ability to scale launch sites. All
aspects of the GS0 launch system are fabricated in ABL’s factory, enabling strict process control andoversight. Importantly, this enables ABL to serially produce launch site infrastructure in the same way thecompany produces launch vehicles. ABL can rapidly create launch infrastructure and deploy it to fixed, FAAapproved launch sites for increased orbital launch capacity.

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GS0 Launch Mount
Horizontal
RS1 Vehicle

GS0 Bulk Storage

GS0 Fluid andElectrical container

Figure 0-2. GS0 system layout

Payload Processing Facilities
For payload processing at various sites, ABL ensures that all facilities meet the following requirements:
§
§
§
§
§
§
§
§
§

ISO 14644 Cleanroom; ISO8 certified
Certified Crane available for use
Adequate ceiling/hook height clearances
Adequate space for GSE, Payload, PAF, PLF, and tables
Gowning room, garments, and supplies
Adequate power for integration activities
Adjacent office facilities with desks, phone lines, internet connectivity, and a printerCompatibility with security requirements
Ability to support hazardous operations

ABL will also provide a storage area for crates and containers after they are unloaded. ABL maintains astandard tool and GSE list for integration needs and will ensure that all necessary tools/equipment are
calibrated properly and available for use during integration. Appropriate safety equipment will be obtainedfor hazardous operations.

Test Facilities
ABL’s Production Test site is located at the Mojave Air and Spaceport, shown in Figure 0-3. This facility
currently includes two active engine test bays, as well as a Stage 2 test stand and a Stage 1 test stand. Thisfacility allows for rapid test setup and execution of all engine acceptance tests leading up to launch.
ABL also has a test facility located at Edwards Air Force Base. This facility is a Development Test Site andincludes an area for general testing, including structural proof testing.

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Figure 0-3: ABL Test Site at MASP with Integrated E2 Cell (left) and E2 Powerhead Cell (right)

LAUNCH OPERATIONSABL begins the deployment of the GS0 ground systems at approximately L-25 days. The launch stool issecured, bulk commodities are staged, and racks for mission control are installed. Ground system activationand checkouts will occur up until L-10 days and happen in parallel with RS1 stage checkouts. Payload arrivaland processing can also begin as early as L-30 days, but notionally could occur as late as L-12 days.
Once S1 and S2 are mated (at approximately L-10 days), the LV is mounted to the launch stool andintegrated checkouts take place, including vehicle HITL tests. At L-5 days, the LV performs a static fire testwith a burn duration of 5 seconds. Post-test, the vehicle is brought back to horizontal, and the Encapsulated
Assembly is mated to RS1 at L-4 days. The Launch Readiness Review is conducted at L-2 days as the final
review before launch.
Table 0-1 illustrates a standard launch campaign timeline. While each mission is different, ABL adheres toa strict launch timeline to enable high-cadence and on-time launches. As arranged in advance, ABL can
accommodate customers that require more time onsite for payload processing.
Table 0-1. Reference Launch Campaign Timeline

Event
GS0 Deployment Begins
LV Arrives at to Launch Site
RS1 Unpacking and Inspection
RS1 Integrated System Checkouts

Date
L-25 days
L-21 days
L-20 days
L-19 days
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Payload Integration Start
Stage Mate
Encapsulation

L-15 days
L-10 days
L-9 Days

Operational Dry-Runs
Static Fire Test
Mate EA to RS1
Pad Fluid and Electrical System Checkouts
Pad Radio Frequency Checkouts
Propellant and Gas Bulk Storage Verification
Launch Readiness Review
LaunchL-7 days
L-5 days
L-4 days
L-3 days
L-3 days
L-3 days
L-2 days
L-0

Payload Processing
ABL’s standard payload arrival time at the payload processing facility is at L-30 days; however, this can be
tailored to the customer’s specific schedule. Depending on the payload processing facility used, ABL will
coordinate for appropriate payload standalone processing and fueling and PAF integration andencapsulation rooms.

Payload Encapsulation
Once final mechanical and electrical mate between the payload and PAF is complete, the entire Payload
and PAF assembly is broken over from vertical to horizontal. The fairing interior and exterior will be cleaned
and staged in the airlock on a mobile cradle. When the payload/PAF assembly is ready, the fairing will bestaged into the cleanroom and aligned for horizontal encapsulation. Alignment and encapsulation occur via
a cradled rail assembly which is attached to the PAF breakover fixture.
When encapsulation is complete, the Encapsulated Assembly (EA) is connected to an HVAC/GN2 purge
and transported and mated to RS1 at the pad.

Security
ABL can accommodate the security requirements for the payload while present at the launch site. This
includes 24/7 video monitoring of key areas, card access control to facilities for approved personnel only,
and 24/7 security patrols that walk the entire site periodically. Additional requirements can be discussed
and arranged in coordination with ABL.

Countdown Operations
ABL executes a rapid “load-and-go” style launch operation. Propellant and gas commodities are loaded
quickly through high-capacity systems to minimize the duration the launch vehicle remains loaded on thepad, reducing risk.
To enable rapid launch, the vehicle and ground systems undergo extensive testing prior to launch day. Thisconsists of a series of HITL and dry-run sequences to verify system functional integrity and timing.
Additionally, stringent leak checks are executed on all fluid systems to ensure a successful propellant load
operation.

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In addition to managing the vehicle, ABL executes other required day-of-launch mission verifications. These
include upper-level wind assessments to tune loads alleviation algorithms, as well as Monte Carlo mission
simulations.

Flight Operations
Liftoff and Ascent
A reference timeline for a sample mission in which Stage 2 performs a single burn, deploys the payload,and subsequently executes a Collision Avoidance Maneuver and a deorbit burn at a safe time after payload
separation is shown in Table 0-2. For higher altitude orbits or multi-manifest missions, RS1 Stage 2 executes
multiple burns.
Table 0-2. Reference Mission Timeline

Mission Time [m:s]
-0:02
0:00
1:18
2:58
3:00
3:04
3:16
7:59
8:37
10:00
15:00

Event
Stage 1 Startup
Lift Off
Maximum Dynamic Pressure (MaxQ)
Main Engine Cut Off (MECO)
Stage Separation
Stage 2 Startup 1
Fairing Separation
Second Engine Cut Off (SECO)
Payload Deploy
Collision Avoidance Maneuver (CAM)
Deorbit Burn

Payload Separation and Reporting
After reaching the spacecraft injection orbit and attitude, the vehicle will issue redundant payload
separation commands to initiate separation of the payload.
ABL understands the importance of locating a payload quickly post-deployment and as such, ABL’s
standard time for post-deployment delivery of the state vector and orbital parameters is within deployment+ 45 minutes, with an emphasis on providing the data as soon as possible. To do this, ABL considers groundstation planning with the mission-specific trajectory to ensure coverage during payload
deployment. If payload deployment does not occur in view of a ground station, or there is a ground station
issue, the RS1 vehicle will store the information on-board until the next available opportunity to transmit to
the ground.

Collision Avoidance
RS1 will provide adequate time between payload separation and any maneuvers which could result incontamination to the payload, such as a collision avoidance maneuver.

Post Launch Reports
Post-launch, ABL provides a report that includes timing of all major events as well as actual versus predictedperformance, orbital injection accuracy, and measurement of the environments in the Payload Fairing.

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DOCUMENT REFERENCE
List of Tables
Table 2-1: Orbital Capabilities ................................................................................................................................................................ 3
Table 2-2. Orbital Parameter Accuracy .............................................................................................................................................5
Table 2-3. Attitude and Body Rates for a Three-Axis Stabilized Deployment .............................................................. 6
Table 3-1. RS1 Overview .......................................................................................................................................................................... 7
Table 5-1. Payload Thermal and Humidity Environments...................................................................................................... 14
Table 5-2. Flight Load Factors ........................................................................................................................................................... 14
Table 5-3. NASA GEVS Protoqualification Levels..................................................................................................................... 15
Table 5-4: Maximum Flight-Level Payload Acoustic Environment ................................................................................... 16
Table 5-5: RS1 Radio Frequency System characteristics ..................................................................................................... 18
Table 5-6. Payload Requirements .................................................................................................................................................... 19
Table 6-1: Example timeline of deliverables from both parties ...........................................................................................21
Table 7-1. United States Launch Sites Details ............................................................................................................................ 23
Table 8-1. Reference Launch Campaign Timeline .................................................................................................................... 26
Table 8-2. Reference Mission Timeline .......................................................................................................................................... 28

List of Figures
Figure 2-1: RS1 LEO Payload Capability ...........................................................................................................................................4
Figure 2-2: Reference mission timing of major events ..............................................................................................................5
Figure 3-1: RS1 Overview ......................................................................................................................................................................... 7
Figure 3-2. LV Coordinate System ......................................................................................................................................................8
Figure 3-3: E2 Sea Level Engine ...........................................................................................................................................................8
Figure 3-4: Avionics manufacturing bay at ABL headquarters ............................................................................................. 9
Figure 4-1: RS1 Dynamic Envelopes for 80” Hammerhead (left) and 108” XL Fairing (right) Options .............. 11
Figure 4-2: PAF 38.81 Inch Mechanical Interface ......................................................................................................................12
Figure 4-3: RS1 Electrical Interfaces.................................................................................................................................................12
Figure 4-4: Payload – Ground Electrical Interface .....................................................................................................................13
Figure 5-1. Reference Mission Acceleration Profile ................................................................................................................. 15
Figure 5-2: NASA GEVS Random Vibration Protoqualification Levels ........................................................................... 16
Figure 5-3: P95/S0 SPL for Fairing Cavity.................................................................................................................................... 17
Figure 5-4: Approximate Shock Response for Payload Separation ................................................................................ 18
Figure 7-1: ABL launch sites, offices, and test facilities .......................................................................................................... 23
Figure 7-2. GS0 system layout ........................................................................................................................................................... 25
Figure 7-3: ABL Test Site at MASP with Integrated E2 Cell (left) and E2 Powerhead Cell (right)...................... 26

List of Acronyms
AcronymDefinition

24/7

Twenty-four hours seven days per week

3DOF

Three Degrees of Freedom

6DOF

Six Degrees of Freedom

ABL

ABL Space Systems
Page 29 of 31

AFSPCMAN

Air Force Space Command Manual

AK

AlaskaATP

Authority to Proceed

BEO

Beyond Earth Orbit

CA

California

CAD

Computer Aided Design

CAM

Collision Avoidance Maneuver

CCSFS

Cape Canaveral Space Force Station

CG

Center of Gravity

CLA

Coupled Load Analysis

EA

Encapsulated Assembly

EAFB

Edwards Air Force Base

EGSE

Electrical Ground Support Equipment

FAA

Federal Aviation Administration

FL

FloridaGEO

Geostationary Earth Orbit

GEVS

General Environmental Verification Standard

GN2

Gaseous Nitrogen

GNC

Guidance, Navigation, and Control

GNSS

Global Navigation Satellite System

GSE

Ground Support Equipment

GTO

Geostationary Transfer Orbit

HDRM

Hold Down and Release Mechanism

HITL

Hardware-in-the-Loop

HVAC

Heating, Ventilation, and Air Conditioning

ICD

Interface Control Document

IMU

Inertial Measurement Unit

KSC

Kennedy Space Center

LC

Launch Complex

LEO
LOx
LV
MASP
MaxQ
MECO
MEO
MTO
NASA
OASPL
PAF
PLF
PSC

Low Earth Orbit
Liquid Oxygen
Launch Vehicle
Mojave Air and Space Port
Maximum Dynamic Pressure
Main Engine Cutoff
Medium Earth Orbit
Mass to Orbit
National Aeronautics and Space Administration
Overall Sound Pressure Level
Payload Attach Fitting
Payload Fairing
Pacific Spaceport Complex
Page 30 of 31

PSD
PTEC
Q
RAAN
RF
SECO
SEIP
SLC
SMC
SPL
SSO
SW
TPL
TRM
TVC
UHF
UK
VSFB
WA

Power Spectral Density
Payload T-0 EGSE Container
Dynamic Pressure
Right Assentation of the Ascending NodeRadio Frequency
Second Stage Engine Cutoff
Standard Electrical Interface PanelSpace Launch Complex
Space and Missile Systems CenterSound Pressure Level
Sun Synchronous Orbit
Space Wing
Third Party Liability
Tactical Responsive Mission
Thrust Vector Control
Ultra-high Frequency
United Kingdom
Vandenberg Space Force Base
Washington

Page 31 of 31