Department of the Navy, Naval Air Systems Command, Aircraft Support Division This announcement is a sources sought notice. The Naval Air Warfare Center Aircraft Division (NAWCAD) Patuxent River, MD is seeking potential sources for information and no cost product samples of commercially available, non-developmental head and neck restraint systems which may have applicability to military aircraft escape systems. Submissions will be evaluated to determine if they have potential to mitigate neck injury during the ejection sequence. Submissions will also be evaluated to confirm that the head mobility needed during normal flight is not inhibited. Of particular interest to the government are items that may do one or more of the following: A) Provide restraint for the head during the initial stages of ejection while the aircrew is in the ejection seat. B) Provide restraint for the head during the later stages of ejection after separation from the seat has occurred. C) Provide aerodynamic shielding for the helmet during the initial stages of ejection while the aircrew is in the ejection seat. D) Decrease head borne mass in an ejection while maintaining head and facial protection. E) Decrease the helmet aerodynamic profile during an ejection while maintaining head and facial protection. This request is for INFORMATION PURPOSES ONLY. CURRENT TECHNOLOGY: Current ejection seat technology provides restraint for the torso, pelvis, arms, and legs up to the time of seat separation from the aircrew. However, there is no restraint provided for the head and neck other than the headpad behind the head. There have been a number of technologies explored for neck protection with varying degrees of success. These have included: divesting helmet mounted devices, venting helmets, tethering helmet to head pad, tethering helmet to shoulders, supporting neck with airbags, aerodynamic brim on head pad, and aerodynamic fences around head pad. FACTORS AFFECTING HEAD AND NECK INJURY RISK: There are a number of factors creating an environment of increased risk of neck injury during ejection. 1) The aviator population has been expanding to include lighter aircrew. Currently ejection seat aircraft are being designed to accommodate male and female pilots from 103 to 245 lbs. A typical 103 lb female will have muscular and skeletal neck structure that can not withstand a great deal of loading without injury. 2) The addition of helmet mounted devices to military aircraft has resulted in ejections with greater head borne masses. This increase in mass results in increased neck loading during the high g loads experienced in an ejection. 3) The addition of helmet mounted devices has resulted in an increased aerodynamic profile of the helmet during ejection. This increase of surface can result in increased neck loading during the high aerodynamic forces experienced in high speed ejections. 4) The fact that there is no restraint for the head and neck during the initial phases of the ejection other than the head pad can lead to high neck loading in an ejection. Even the limited restraint provided by the head pad is sometimes lost when the head goes around the side of the head pad. 5) The fact that there is no restraint for the head and neck after separation from the seat can lead to high neck loads during parachute opening shock. PURPOSE: Product samples and supporting information provided in response to this announcement will be reviewed to determine whether the device provided has potential to mitigate one or more of causes listed above. All devices should have a minimal detriment on the pilot’s ability to physically perform their flight tasks which includes extensive head and neck motion during the course of a mission. Those submittals which show the most promise will be tested by the government with the goal of evaluating the devices effectiveness in reducing injury risk throughout the entire ejection event. Test methods employed may include but not be limited to windblast tests to simulate aerodynamic effects during the initial stages of ejection and horizontal accelerator tests to simulate effect inertial loading during the catapult, drogue, and parachute opening shock phases of ejection. In addition to testing, integration assessments may be performed to examine the potential for the device to interface with the full range of aircrew anthropometry, aircrew equipment, ejection seat equipment and the aircraft cockpit. Data gathered from these tests will not only help the government to determine the current state of technology in this area, it will also provide a basis for developing requirements for any future efforts to procure head and neck restraint devices. INFORMATION AND MATERIALS REQUIRED: Interested parties will be asked to provide at least two product samples to support the testing and assessments outlined above. In addition, written submittals of test data, design information, performance limitations or instructions for use would be helpful in determining the potential benefits of the device and insuring it is tested in a way which fully evaluates its performance. The written information is key to determining whether the system has merit and warrants further testing. Submittal Information: This IS NOT a Request For Proposal nor does the government intend to pay for any information/items submitted in response to this synopsis. This synopsis does not commit the government to award any future contracts. Interested sources should send product samples and related information to NAWCAD by 15 February 2006. The product samples and information should be sent to Matthew Conrad,NAWCAD Bldg. 2187 Suite 1280, 48110 Shaw Road Unit 5, Patuxent River MD 20670. Product samples will be returned only at the source’s request and expense unless the samples are destroyed during testing. Test data obtained on a submitted device will be shared with the source and if requested, a debrief of the governments findings will be provided. All technical questions must be submitted in writing and mailed to the above address or emailed to the POC provided below. POINT OF CONTACT: Mathew Conrad, Escape Systems Engineer, Phone: (301) 342-8454, Fax: (301) 342-8503, Email
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