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RECORD OF REVISIONS

REV DESCRIPTION DATE

Basic Basic Issue July 24, 2009

A ERB-09-102-2(7/7/2011): 

1. Update 6.2.2 to remove CubeSat structural 

qualification requirement, 

2. Update 6.2.3 and 6.3.3 to allow any sized 

CubeSats between 1U and 3U, 

3. Update Table 1 for clarity, 

4. Editorial corrections. 

October 13, 2011

B PRCB 7/12/2013

1. Update 5.1.12 to allow waivers per LSP-P-317.01

PRCB 11/15/2013 - ERB-09-102-3 (7/11/13)

1. Changed all instances of “PPOD” to “Dispenser” 

2. Update 6.2.4 to allow CubeSat pressure containers

3. Update 6.2.9 to allow CubeSat real time clocks

4. Editorial Corrections

PRCB 12/13/2013 – ERB-09-102-4 Reconvene

1. Update 6.2.3 to increase CubeSat upper size limit 

to 6U. 

2. Update 6.2.1 CubeSat T-Vac not required if 

specified by LSP

3. Update 6.2.11 to 3 inhibits for RF Transmission. 

This change is effective for CubeSat Launch 

Initiative call 6 and subsequent calls.

4. Terminology Clarification pressurant to “contents”

January 30, 2014

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Table of Contents 

1. Introduction..............................................................................4 

2. Applicable Documents................................................................5 

3. Definitions................................................................................6 

4. Mission Objective......................................................................7 

5. Programmatic Requirements........................................................7 

6. Program Technical Requirements..................................................8 

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1. Introduction 

1.1. Purpose 

The purpose of this document is to define the Launch Services Program (LSP) program 

level and technical requirements placed on containerized CubeSat dispenser and 

Picosatellite (CubeSats) satellites for integration on NASA LSP ELV mission. These 

requirements are to ensure no increase in baseline risk to the Primary Mission. The 

requirements within this document are generic and independent of the Launch Vehicle 

(LV). The technical requirements contained in the document will be either implemented 

or flowed down to mission specific dispenser Interface Control Documents (ICDs) as 

well as dispenser and CubeSats specification documents. 

It is the responsibility of the LSP to provide Certification of Flight Readiness (CoFR) 

statements for the integrated dispenser systems that fly on NASA ELV missions. LSP 

will perform verification of the LV to dispenser and the dispenser to CubeSat ICD 

requirements. LSP will have insight into all other CubeSat development activities such 

as design, development, testing and integration. 

1.2. CubeSat Concept 

The CubeSat Project was developed by California Polytechnic State University, San 

Luis Obispo (Cal Poly) and Stanford University's Space Systems Development Lab. 

The Project is an international collaboration of universities, high schools, and private 

firms developing picosatellites containing scientific, private, and government payloads. 

The primary mission of the CubeSat program is to provide access to space for small 

payloads. Cal Poly standardized the form factors for the CubeSat and the most 

common is a 1U, which is a approx. 10 cm cube. There are multiple CubeSat 

configurations based on the 1U form factor such as a 2U (22cm x 10cm x 10cm), 3U 

(34cm x 10cm x 10cm), 6U (34cm x 20cm x 10cm) etc. 

1.3. Dispensers Description 

The dispenser provides a standard interface between picosatellites class satellites and 

a launch vehicle. It also serves as a deployment system for the CubeSats. 

The dispensers are a standard CubeSat deployment system, which ensures all 

CubeSat developers conform to a common CubeSat form factor 1U (10cm x 10cm x 

10cm), which in turn reduces cost and development time. The most common dispenser 

has an internal volume of 34cm x 10cm x 10cm, and is called a 3U dispenser. There 

are other dispensers in industry using the CubeSat form factor of 6U which has an 

internal volume of 34cm x 20cm x 10cm. Other larger CubeSat dispensers are in 

development today that are consistent with the Cubesat form factor of 12U and 24U. 

The dispensers are versatile, with a small profile and the ability to mount to different 

launch vehicles in a variety of configurations and hold differing CubeSat form factors. 

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The design of the dispensers creates a predictable linear trajectory for the picosatellites 

resulting in a low spin rate upon deployment. The launch vehicle sends a signal to 

open a spring-loaded door, then the satellites are deployed from the dispenser by 

means of a spring and glide along smooth flat rails as they exit the dispenser. 

2. Applicable Documents 

All Compliance and Reference documents are compiled into this section. Documents listed 

herein are applicable to this document to the extent specified in the requirement. 

2.1. Compliance Documents 

a. AFSPCMAN 91-710 Range Safety User Requirements Manual Volume 

3 – Launch Vehicle, Payloads, and Ground Support 

Systems Requirements 

b. MIL-STD-1540C Military Standard Test Requirements for Launch, 

Upper-Stage, and Space Vehicles 

c. NASA-STD-6016 Standard Materials and Processes Requirements 

for Spacecraft 

d. NPR 8715.6 NASA Procedural Requirements for Limiting Orbital 

Debris

2.2. Reference Documents 

a. LSP-P-321.01 Engineering Review Process (ERP) 

b. LSP-P-317.01 Dispenser and CubeSat Program Level 

Requirements Violation and Waiver Process 

c. GSFC-STD-7000 General Environmental Verification Standard 

(GEVS) for GSFC Flight Program and projects 

d. JPL D-26086D Environmental Requirements documents (ERD) 

e. MMPDS Metallic Materials Properties Development and 

Standardization 

f. MIL-HDBK-5 Military Handbook 5, Metallic Materials and 

Elements for Aerospace Vehicle Structures 

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3. Definitions 

Primary Mission: All hardware, software, systems, and analysis products pertaining to the 

manifested primary spacecraft customer (includes both primary and secondary payloads). 

Auxiliary Payload: Are considered in this document as the picosatellites or CubeSats that 

have no interface (mechanical, electrical or RF) with the LV. 

CubeSat(s): All hardware, software, systems, and analysis products pertaining to a Cube 

Satellite that is intended to be installed within a dispenser. This includes CubeSat mass 

simulators. 

Dispenser(s): All hardware, software, systems, and analysis products pertaining to a 

CubeSat Deployer. 

Dispenser System: An integrated system consisting of dispenser and installed CubeSats. 

Launch Vehicle (LV): The selected Launch Vehicle for a specified CubeSat mission. 

Launch Services Program (LSP): The NASA Launch Services Program. 

Mandatory Compliance Requirements (MCRs): Are those requirements within the dispenser 

to CubeSat ICD, which LSP is required to verify to sign the CoFR. 

Maximum Predicted Environment (MPE):

 Dynamic Environments MPE: Envelopes a P95/50 or mean + 5 dB of flight 

environments. 

 Thermal MPE: Derived via simulation + 11° C for uncertainty 

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4. Mission Objective 

The LSP desires to launch CubeSats utilizing containerized dispensers as an auxiliary 

payload. 

5. Programmatic Requirements 

Dispenser systems shall pose no increase to the baseline risk for the Primary Mission. 

5.1. Program Requirements 

5.1.1. LSP will procure integrated services and flight qualified dispensers per the 

requirement in this document and mission specific Dispenser to LV ICD. 

5.1.2. LSP will apply best effort for the mission success of the individual CubeSats 

(LSP is not responsible for mission success of the CubeSats). 

5.1.3. CubeSat mission will be approved by the Flight Planning Board before 

manifesting on NASA missions. 

5.1.4. Flight Planning Board will inform the Primary Mission that CubeSats have been 

manifested on their mission. 

5.1.5. LSP will provide resources to accommodate the integration of selected CubeSats 

mission. 

5.1.6. LSP will not require attendance from the Primary Mission for Dispenser or 

CubeSat reviews and assessments; however, the Primary Mission will be 

informed and invited. 

5.1.7. LSP will have approval authority for dispensers and CubeSat requirements and 

insight into all other dispenser and CubeSat development activities (e.g. design, 

development and test) as required. 

5.1.8. CubeSats will be manifested per Manifesting Policy (TBD). 

5.1.9. CubeSats will not interfere with the mission success of other CubeSats 

integrated in the same dispenser. 

5.1.10. CubeSats shall be delivered to the integration contractor in a time frame that 

does not affect the dispenser integration-processing schedule. 

5.1.11. Dispenser system shall be delivered to Launch Service Contractor in a time 

frame that does not affect the Primary Mission integration cycle or launch 

timeline. 

5.1.12. All violations of the requirements listed in this document shall be reviewed and 

dispositioned per LSP-P-317.01, Dispenser and CubeSat Program Level 

Requirement Violation and Waiver Process. All technical requirement changes 

shall be approved by LSP Engineering Review Board. 

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6. Program Technical Requirements 

This section defines the technical requirements for LSP, CubeSats, dispensers and LV. 

6.1. LSP Technical Requirements 

6.1.1. LSP will conduct verifications for the Dispenser to LV ICD as well as the MCRs 

with the Dispenser to CubeSat ICD. 

6.1.2. LSP will follow their standard review process for non-conformances, new flight 

items, changes is qualification status etc. per LSP-P-321.01 Engineering Review 

Process (ERP). 

6.2. CubeSat Technical Requirements 

6.2.1. CubeSats shall be designed, and verified to the environments defined in Table 1 

- Dispenser and CubeSat Test Environments Testing Table and per Figure 1 - 

Dispenser and CubeSat Qualification and Acceptance Test Flow Diagram. 

6.2.2. CubeSat Structural qualification is adequately achieved through environmental 

testing only. (PR 6.3.1, Table 1) During periods where all flight loads are 

applied, CubeSats are considered to be internal components of the dispenser 

assembly. 

6.2.3. CubeSats shall be no smaller than a 1U (10x10x10cm) form factor and no larger 

than a 6U (30x20x10cm) form factor. (dimensions are nominal) 

6.2.4. CubeSats shall not contain pressurized vessels. CubeSat containing nonventable pressure containers are permitted if the satisfy the following 

requirements. 

6.2.4.1. Pressure shall be no more than 1 atmosphere while on Orbit. 

6.2.4.2. Pressure container contents shall be not endanger personnel or 

equipment or create a mishap (accident) if released. 

6.2.4.3. Pressure containers shall be structurally qualified in accordance with 

Table 2 - Strength Qualification Requirements 

6.2.5. CubeSat shall not contain propulsion systems. 

6.2.6. CubeSats shall not contain radioactive material. 

6.2.7. CubeSats shall not contain any explosive devices 

6.2.8. CubeSats hazardous material shall conform to AFSPCMAN 91-710, Range 

Safety User Requirements Manual Volume 3 – Launch Vehicles, Payloads, and 

Ground Support Systems Requirements. 

6.2.9. CubeSats shall remain powered off from the time of delivery to LV through on 

orbit deployment. Real time clock circuits are permitted if they satisfy the 

following requirements. (Reference ELVL-2013-0043486) 

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6.2.9.1. Real time clock circuits shall be isolated from the CubeSats main power 

system. 

6.2.9.2. Real time clock frequencies shall be less than 320 kHz. 

6.2.9.3. Real time clock circuits shall be current limited to less than 10 mA. 

6.2.10. CubeSats shall not radiate RF from the time of delivery to LV through 45 

minutes after on-orbit deployment. 

6.2.11. CubeSats shall be designed with at least 3 independent inhibits to prevent 

inadvertent RF transmission. 

6.2.12. CubeSats shall be self-contained, and provide their own power, sequencing, 

and wiring. 

6.2.13. CubeSats shall be designed to accommodate ascent venting per Ventable 

Volume/Area < 2000 inches in accordance with accepted standards such as 

JPL D-26086, Revision D, Environmental Requirements Document (ERD). 

6.2.14. CubeSats mission design and hardware shall be in accordance with NPR

8715.6 NASA Procedural Requirements for Limiting Orbital Debris. 

6.2.15. CubeSats materials shall be selected in accordance with NASA-STD-6016

(Section 4.2), Standard Materials and Processes Requirements for Spacecraft. 

6.3. Dispenser Technical Requirements 

6.3.1. Dispensers shall be designed, and verified to the environments defined in Table 

1 - PPOD and CubeSat Test Environments Testing Table and per Figure 1 - 

Dispenser and CubeSat Qualification and Acceptance Test Flow Diagram. 

6.3.2. Dispensers shall be structurally qualified in accordance with Table 2 - Strength 

Qualification Requirements. 

6.3.3. CubeSat size limitations are established in 6.2.3 and occupy the full usable 

volume of a Dispenser. 

6.3.4. Dispensers shall not violate the primary mission static and/or dynamic 

envelopes. 

6.3.5. Dispensers shall not affect LV avionics qualification status or architecture. 

6.3.6. Dispensers shall incorporate a sensor for door position (Open/Closed). 

6.3.7. Dispensers’ door release mechanism shall be designed to accept redundantly 

initiated signals. 

6.3.8. Dispensers shall be designed to accommodate ascent venting per Ventable 

Volume/Area < 2000 inches in accordance with accepted standards such as 

JPL D-26086, Revision D, Environmental Requirements Document (ERD).

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6.3.9. Dispensers shall deploy CubeSats at a velocity sufficient to prevent re-contact 

with Primary Mission hardware. 

6.3.10. Dispensers shall not deploy CubeSat mass simulator(s). 

6.3.11. Dispensers shall utilize industry standards for locking methodologies on all 

fasteners consistent with NASA-STD-6016. 

6.3.12. Dispensers’ material shall be in accordance with NASA-STD-6016 (Section 4.2), 

Standard Materials and Processes Requirements for Spacecraft.

6.3.13. Dispensers shall conduct vehicle specific CubeSat separation analyses. 

6.3.13.1. The separation analysis shall determine the nominal and 3 sigma 

dispersion values of the impulse imparted to the LV for each CubeSat 

separation event to include consideration of separation system 

mechanism and CubeSat mass properties uncertainties. 

6.3.13.2. The separation analysis shall confirm that deploying CubeSat(s) during 

the CubeSat separation event(s) remain within the allowable separation 

cone(s) as specified by the LV contractor. 

6.3.14. Dispenser System shall be designed to provide a minimum of 20 dB EMI Safety 

Margin (EMISM) for non-explosive actuator (NEA) circuits. 

6.3.15. Dispenser System shall have a fixed base frequency greater than 120 Hz. 

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Table 1 – Dispenser and CubeSat Environments Test Table 

Tests Qualification by Test Protoflight Test Acceptance Test

Random 

vibration6

(CubeSat and 

Dispenser)

Ref Mil-Std 1540C

MPE + 6 dB for (3) minutes, each 

of (3) axes 1

MPE+3 dB for (2) minutes, each of 

(3) axes 1

MPE for (1) minute, each of (3) axes 

1

Sinusoidal 

Vibration6

(CubeSat and 

Dispenser)

Ref Mil-Std 1540C

MPE + 6 dB. Testing shall be 

performed for content that is not 

covered by random vibration 

testing 

1.25 x MPE. Testing shall be 

performed for content that is not 

covered by random vibration testing 

MPE. Testing shall be performed for 

content that is not covered by 

random vibration testing 1

Shock6

(CubeSat and 

Dispenser)

Ref Mil-Std 1540C

MPE + 6 dB, 3 times in both 

directions of 3 axes 1, 3

MPE + 3 dB, 1 times in both 

directions of 3 axes 1, 3

N/A

Thermal 

Vacuum Cycle

(Dispenser Only)

Ref.: MIL-STD 

1540 B,

GSFC-STD-7000

MPE2 +/- 10° C 

Minimum Range = -14 -3/+0°C to 

+71 -0/+3°C 

Cycles = 8 

Dwell Time = 1 hour min. @ 

extreme Temp. after thermal 

stabilization

Transition = < 5° C/minute

Vacuum = 1x10-4 Torr

MPE2 +/- 10° C 

Minimum Range = -14 -3/+0°C to 

+71 -0/+3°C 

Cycles = 4 

Dwell Time = 1 hour min. @ extreme 

Temp. after thermal stabilization

Transition = < 5° C/minute

Vacuum = 1x10-4 Torr

MPE2 +/- 5° C 

Minimum Range = -9 -3/+0°C to 

+66-0/+3°C 

Cycles = 2 

Dwell Time = 1 hour min. @ extreme 

Temp. after thermal stabilization

Transition = < 5° C/minute

Vacuum = 1x10-4 Torr

Thermal 

Vacuum Bake 

out

(Dispenser Only)

Ref.: MIL-STD 

1540 B,

GSFC-STD-7000

N/A Min. Temp 70°C 4, 7

Cycles = 1 

Dwell Time = Min. 3 hour after 

thermal stabilization

Transition = N/A

Vacuum = 1x10-4 Torr

Min. Temp 70°C 4, 7

Cycles = 1 

Dwell Time = Min. 3 hour after 

thermal stabilization

Transition = N/A

Vacuum = 1x10-4 Torr

Thermal Vac

Bake out

(CubeSat Only)

Ref.: MIL-STD 

1540 B,

GSFC-STD-7000

N/A Min. Temp 70°C 5, 8

Cycles = 1 

Dwell Time = Min. 3 hour after 

thermal stabilization

Transition = < 5° C/minute

Vacuum = 1x10-4 Torr 

Min. Temp 70°C 5, 8

Cycles = 1 

Dwell Time = Min. 3 hour after 

thermal stabilization

Transiton = < 5° C/minute

Vacuum = 1x10-4 Torr

Hardware 

Configuration

Dispenser – Flight identical unit 

(includes NEA, cable and 

connector)

CubeSat – Flight Identical unit

Dispenser – Flight unit (includes 

flight NEA, cable and connector)

CubeSat – Flight unit

Dispenser – Flight unit (includes 

flight NEA, cable and connector)

CubeSat – Flight unit

(1) Dynamic Environments random MPE envelopes a P95/50 or mean + 5 dB of flight environments. Sinusoidal levels envelope loads 

predictions and flight environments. Shock MPE envelops P95/50 for at least (3) samples, with 4.5 dB uncertainty factor applied 

where less than (3) samples are used.

(2) Thermal MPE = Max predicted via simulation + 11° C for uncertainty.

(3) Shock testing is not required when the following conditions are met: 1) The qualification random vibration test spectrum when

converted to an equivalent shock response spectrum (3-sigma response for Q=10) exceeds the qualification shock spectrum 

requirement at all frequencies below 2000 Hz. 2) The maximum expected shock spectrum above 2000 Hz does not exceed (g) 

values equal to 0.8 times the frequency in Hz at all frequencies above 2000 Hz, corresponding to the velocity of (50 inches/second).

(4) Maximum bake out temperature set to same maximum temperature for thermal cycle test for consistency, assuming bake out would 

be performed during same vacuum exposure.

(5) If the CubeSat cannot achieve these temperature levels, the CubeSat shall hold a minimum temperature of 60°C for a minimum of 6 

hours. 

(6) Levels are defined to be at the dispenser to Launch Vehicle mechanical interface.

(7) Thermal bake out temperatures are not to exceed qualification temperatures

(8) CubeSat Thermal vacuum bakeout is required unless LSP removes the requirement for individual CubeSats based on 

material selection, quantities and manifesting.

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Figure 1 Dispenser and CubeSat Qualification Acceptance Flow Diagram 

Table 2, Strength Qualification Requirements 

Qualification Method Qualification Factors of Safety

Strength Analysis Only 1.6 X Limit load with respect to material yield 

strength

2.0 x limit load with respect to material ultimate 

strength

Structural Test* 1.1 X Limit load with respect to material yield 

strength with no detrimental yielding of test article

1.25 x limit load with respect to material ultimate 

strength with no structural failure of test article

Note: Material Strength properties shall be "A" basis allowable as shown in either MIL-HDBK-5 or MMPDS. 

Limit loads are worst-case combination of flight loads and environments occurring during the launch phase of 

a mission. 

* A combination of structural test and analysis maybe used for qualification. Factors of safety used in the 

analysis are those shown above for Structural Test.

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6.4. LV Technical Requirements 

6.4.1. LV shall integrate and/or install Dispenser System onto a NASA/Launch Vehicle 

Contractor agreed upon location. 

6.4.2. LV integration of a dispensers System shall not delay primary mission 

integration cycle. 

6.4.3. LV shall not modify the Primary Spacecraft interface to accommodate a 

Dispenser. 

6.4.4. LV shall accommodate Dispenser door position indicator in the flight telemetry 

stream. 

6.4.5. Deleted 

6.4.6. LV shall provide fault tolerance for inadvertent actuation equal to or better than 

that used on the primary/secondary spacecraft. 

6.4.7. LV shall not alter the mechanical and electrical interface design of the 

Dispensers. 

6.4.8. LV shall design, qualify and acceptance test the LV Dispenser interface. 

6.4.9. LV shall command deployment of the dispenser’s CubeSats.

6.4.10. LV trajectory design shall not result in LV contact with deployed CubeSats. 

6.4.11. LV shall not deploy the CubeSats in a trajectory that will contact the Primary 

Mission or LV. 

6.4.12. LV shall define the CubeSat allowable deployment cone for each dispenser. 

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Appendix A 

Acronyms

Cal Poly California Polytechnic State University 

cm Centimeter 

ELV Expendable Launch Vehicle 

ICD Interface Control Document 

kg Kilograms 

LSP Launch Services Program 

LV Launch Vehicle 

MCR Mandatory Compliance Requirements 

MPE Maximum Predicted Environments 

NEA Non-Explosive Actuator 

RF Radio Frequency 

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