Liquid Apogee Engine (LAE) Propulsion Capability Study

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Liquid Apogee Engine (LAE) Propulsion Capability Study

Liquid Apogee Engine (LAE) Propulsion Capability Study has been closed on 04 Oct 2019. It no longer accepts any bids. For further information, you can contact the Department of the Air Force

Bellow, you can find more information about this project:

Location: United States

General information

Donor:

Department of the Air Force

Industry:

Transport & Logistics

Manufacturing

Construction & Engineering

Status:

Closed

Timeline

Published:

19 Sep 2019

Deadline:

04 Oct 2019

Value:

Not available

Contacts

Email: [email protected]
[email protected]

Description

Solicitation Number:

Notice Type:

Synopsis:

Added: Sep 19, 2019 5:28 pm

In accordance with (IAW) FAR 5.201 and 5.203(a), this is a Pre-Solicitation notice for a proposed contract action where the Government intends to solicit and negotiate with only one source. IAW FAR 5.207(c)(16), any responsible sources may submit a capability statement or proposal which shall be considered by the agency.
In accordance with (IAW) FAR 6.302-1(a)(2)(iii)(A-B), the Department of the Air Force, Space and Missile Systems Center (SMC), Space Development Contracting branch (SMC/DCK), located at Los Angeles AFB, CA, intends to award a new sole source contract to Aerojet Rocketdyne (Redmond, WA 98052). IAW DFARS PGI 206.302-1(d), a request for information notice for this requirement was previously posted on FBO on 10 April 2019. A copy of the Justification & Approval (J&A) is attached to this FBO notice.

This effort is for engineering services, regarding the research and development of the 100-lbf LAE up to a qualification test report to verify Government 100-lbf LAE requirements. As a result of the negotiated sole source contract, the LAE effort will include the following minimum capabilities:

1. Domestic Vendor
2. 100-lbf (440N) of thrust
3. Using hydrazine fuel and NTO oxidizer
4. Specific impulse >320 seconds
5. Total qualified lifetime of 9 hrs of firing time in a vacuum environment (number already includes margin)
6. Capable of implementation on any prime contractor's bus (Boeing, LM, NGIS). This affects environmental capability including shock and vibration. This also affects the range of inlet pressures that the unit must operate across.
7. Capable of operation at propellant/hardware temperatures up to 51°C (minimum) / 61°C (goal). Note that these temperatures include uncertainty and qualification margin so that implementation in a satellite design has flight capability to 30°C min / 40°C goal.
8. Qualification testing complete within 2 years to provide a mature LAE platform for future space platforms and funding constraints.

Projected Request-for-Proposal (RFP) release date for this requirement is estimated to be no sooner than 15 calendar days after this Pre-Solicitation notice is posted, and will be directed solely to the prospective source identified.

This notice expires 15 days after publication.