A -- 2.75-INCH ROCKET DIGITAL LAUNCHER POWER, COMMUNICATIONS AND IDENTIFICATION INTERFACE PORT

Notice Date

June 28, 2001

Contracting Office

Commander, U.S. Army Aviation and Missile Command, Acquisition Center, Research Development and Engineering Center, Redstone Arsenal, AL 35898-5000

ZIP Code

35898-5000

Solicitation Number

NA

Response Due

August 14, 2001

Point of Contact

Mr. John Mason, Contract Specialist, (256) 842-7260, e-mail: john.mason@redstone.army.mil/, or Ms. Patsy Garrison, Contracting Officer, (256-842-7406, e-mail: patsy.garrison@redstone.army.mil/. Technical point of contact Don Davis, (256)876-5089, e-mail: don.davis@redstone.army.mil .

Description

The U.S. Army Aviation and Missile Command (AMCOM) is soliciting potential sources for, "2.75-Inch Rocket Digital Launcher Power, Communications and Identification Interface Port." Sponsoring agency -- US Army Aviation & Missile Command, Research, Development and Engineering Center, Propulsion and Structures Directorate, AMSAM-RD-PS-SA, Redstone Arsenal, AL 35898. Any questions may be e-mailed to the Contract Specialist above, who will coordinate responses with the Technical Point of Contact. This sources sought does not constitute a solicitation of proposal. Authority to enter into negotiations to award a contract for the contemplated effort has not been received and funds are not currently available. The Aviation and Missile Command (AMCOM) Research, Development, and Engineering Center (RDEC), as the 2.75 Inch Rocket Launcher Design Agency, is preparing for the development of the next generation rocket launcher for the 2.75 Inch (or HYDRA 70) Rocket System (also called ROCKET XXI). The next generation of free flight and guided 70mm rockets will require both power and two-way communications between the rockets and the launcher. A key part of the next generation launcher will be a multifunction interface port between the rockets and the launcher electronics. The RDEC is seeking concepts for this interface port. This port may be either a series of specialized modules or a single multi-functional unit that includes all of the functions described below. Wireless concepts are preferred, but design approaches that utilize a multi-wired umbilical or automatic contacts in the launch tube will be given full consideration. Currently, the United States Army, Navy, and Air Force use 7 and 19 tube launchers. The next generation launcher may have as few a 4 and as many as 25 launch tubes. Cost will be a major driver, as each launch tube will require an interface port. In order to assure compatibility, the interface port concepts must include a notional design for both the launcher side and rocket sides of the interface. The interface port will operate in conjunction with a launcher electronics package that in turn communicates with the weapons platform through a MIL STD 1760 connector. The launcher electronics package is already under development by the U.S. Navy in a parallel program. The interface port must perform the following functions: 1) Provide pre-launch power to the warhead/guidance section of the rocket; 2) Provide two-way communications for passing guidance data, Built In Test (BIT) commands, BIT results, status, future digital fusing signals, and other essential data; 3) To allow the use of existing remote set fuse rockets, the interface will include the current fuse connector on the forward face of the launcher; 4) Automatically determine rocket/warhead type loaded into each tube for automatic inventory and so that the launcher electronics can service each rocket with the correct signals. (Built-in characteristics in fuzes, bar codes, the newer Radio Frequency Identification (RFID) technologies are considered likely candidates if there are viable concepts for implementing them.) The interface ports will be located on the outside of the aluminum launch tubes. Any contacts will minimize penetration into the tube; if possible, contacts should retract when the rocket is fired and engage only when the rocket is fully seated. Power and communications interface point(s) must be located forward of the rocket motor/warhead joint. For rockets with remote fuses, such as the improved digital M439 fuse, the interface port will not change the fuse setting function, only the signal path. The rocket identification device may be co-located with the power and communications devices, or at any location along the tube as long as the position is well defined. It is desirable that the means of rocket identification be capable of being retrofitted to existing stocks of rockets. It is desired that all connections with the rockets be automatic; i.e., no action required on the part of loaders beyond securing the rocket into the tube. Components on the rocket side of the interface must be flush mounted and not extend beyond the 2.75-inch diameter of the rocket. Communication to and from the rockets must not be detectable outside the launcher. There cannot be any "cross-talk" between tubes due to "leaking" signals. For the present, the actual firing signal will NOT be sent through the interface port; the firing signal will use the current MK66 firing contact band with coordination taking place in the launcher electronics. The interface port must function in the launcher environment, which is characterized by helicopter driven vibration, and ambient temperatures that range from -50oF to 150oF, with internal temperatures rising to as high as 500oF in approximately 1 second when rockets are fired. The interface port must also function in the standard military environment; environmental testing of the final product will be tested per MIL STD 810F. Rocket exhaust products may be deposited on the inside of the launch tubes and on any windows in the tube walls. The launcher may have to fire several loads of rockets before conditions permit cleaning. Any "windows" or holes in the tube walls should be kept to a minimum and must be sealed against rocket exhaust gases. Any window seals must be resistant to solvent and abrasive effects of standard bore cleaning materials and procedures, as well as the passing rocket blast. It is expected that the launcher will be usable for at least 25 full loads, without repair. When a rocket is fired, all interior surfaces of the launch tubes are briefly exposed to exhaust flame temperatures of up to 3800oF moving along the tube axis in excess of Mach one. The launcher, with the interface port installed, and loaded with rockets with functional interfaces, must meet the Electro-Magnetic Interference requirements of MIL- STD 461E. The interfacing module(s) must fit in the space between the launch tubes. This space is defined by three tubes with a radius of 1.44 inches, in a triangular arrangement, with the tubes on 3.03 inch centers. The aluminum launch tubes are .032 inches thick. The forward 8 inches of the tubes will also have a doubler (this acts as a heat sink) that is also .032 inches thick. It should be assumed that the rockets will be free to rotate in the tube during carriage prior to firing. Because of this, the rocket may be in any random orientation when the interface port is functioning unless a means is provided to secure the rocket in a known, fixed orientation. Offerors should submit an abstract with Rough Order of Magnitude (ROM) estimates of cost and time required to accomplish design, analysis, test & fabrication. AMCOM may request a full proposal from offerors whose abstract looks promising. A successful offeror may be invited to become part of an Integrated Product Team for developing the next generation launcher. Solicitation of a full proposal does not assure the award of a contract. The abstract should consist of a title and a summary of up to ten pages. The title page should state "Proposal Abstract for 2.75 Inch Rocket Digital Launcher Power, Communications and Identification Interface Port", the offeror's point of contact with telephone and facsimile numbers, and the signature of an authorized company officer. The summary should clearly describe a design concept to meet the requirements described above with material selection for each significant component identified. It should address maturity and risk level of technology proposed. It should include offerors experience regarding design and analysis of similar or related structural assemblies. Interested sources that can meet the requirement and desire to be considered must respond within 45 calendar days with their abstract. All proprietary data should be clearly marked and will be held in the strictest confidence. Responses will be disposed of in a manner that protects proprietary data. Firms responding should indicate whether they a U.S. or foreign-owned firm. Disclosure of classified and export-controlled unclassified, including sensitive unclassified information, shall be denied to Foreign Governments and Foreign Nationals, including firms under foreign ownership, influence, or control, even if the firm has been granted a reciprocal industrial security facility clearance. Abstracts should be sent to the U.S. Army Aviation and Missile Command, ATTN: AMSAM-AC-RD-BB, John Mason, Building 5400, Redstone Arsenal, AL, 35898. This synopsis is for information and planning purposes, does not constitute a Request for Proposals, and is not to be construed as a commitment by the Government.

Record

Loren Data Corp. 20010702/ASOL010.HTM (W-179 SN50Q327)