SOLICITATION NOTICE
A -- SPACECRAFT INSTRUMENTATION TO MEASURE AND STIMULATE SPACE PARTICLES AND PLASMA WAVES IN THE MEDIUM EARTH ORBIT REGIME
- Notice Date
- 3/25/2004
- Notice Type
- Solicitation Notice
- Contracting Office
- ESC/PKR, R&D Contracting, 104 Barksdale, Hanscom AFB, MA 01731-1806
- ZIP Code
- 01731-1806
- Solicitation Number
- PRDA-AFRL-VSBo4-01
- Response Due
- 5/10/2004
- Archive Date
- 5/10/2004
- Point of Contact
- John W Flaherty 781-377-2529
- E-Mail Address
-
Email your questions to Click Here to E-mail the POC
(john.flaherty@hanscom.af.mil)
- Small Business Set-Aside
- N/A
- Description
- NA NAME: Technical: Dr. Bronislaw Dichter, AFRL/VSBXR, Tel 781-377-3991, email Bronek.Dichter@hanscom.af.mil Contracting: Mr. John Flaherty, ESC/PKR, Tel 781-377-2529, email John.Flaherty@hanscom.af.mil CLASSIFICATION CODE: A - Source Sought Synopsis ADDRESS: Technical: Dr. Bronislaw Dichter, Air Force Research Laboratory, AFRL/VSBXR, 29 Randolph Rd Hanscom AFB MA 01731-3010 Contracting: Mr. John Flaherty, Electronic Systems Center, R&D Contracting Division, ESC/PKR, 104 Barksdale St, Bldg 1520, 3rd floor, Hanscom AFB MA 01731-1806 TITLE: SPACECRAFT INSTUMENTATION TO MEASURE AND STIMULATE SPACE PARTICLES AND PLASMA WAVES IN THE MEDIUM-EARTH ORBIT (MEO) REGIME SOLICITATION NUMBER: PRDA #AFRL/VSB04-01 RESPONSE DATE: 10 May 2004 CONTACT POINT: Technical: Dr. Bronislaw Dichter, Air Force Research Laboratory, AFRL/VSBXR, 29 Randolph Rd Hanscom AFB MA 01731-3010 Contracting: Mr. John Flaherty, Electronic Systems Center, R&D Contracting Division, ESC/PKR, 104 Barksdale St, Bldg 1520, 3rd floor, Hanscom AFB MA 01731-1806 SUBMISSION TYPE: DESCRIPTION. The Battlespace Environment Division, Space Vehicles Directorate, Air Force Research Laboratory is interested in receiving proposals related to the development and on-orbit demonstration of spacecraft instrumentation for the in-situ measurement, global characterization and stimulation of space particles and plasma in the Medium Earth Orbit (MEO) regime, nominally defined as approximately 6000 km perigee, 12000 km apogee with inclination between 0 - 70 degrees. Measurements of particle populations should include spectral resolution over the following ranges: cold plasma; low energy electrons and protons (100 ev - 50 keV); medium energy electrons (50 keV - 1 MeV); high energy trapped electrons (1 MeV - 30 MeV); loss cone electrons (100 - 500 keV), medium energy protons (50 keV - 10 MeV); and high energy trapped protons (10 MeV - 450 MeV). Local pitch-angle distributions should be measured for the trapped particle populations and the DC magnetic field determined to enable mapping of local measurements to other magnetospheric locations. The local plasma index of refraction should be determined using measurements of the DC magnetic field and cold plasma density. Dosimetry measurements behind a range of shielding between 0.08 and 0.25 inches of aluminum with differentiation between electron and proton generated dose are desired. Models of instrument response to expected environment conditions are desired in order to better calibrate and interpret the data. Instrumentation should be provided to measure the amplitude and mode structure of the in-situ plasma wave field in the 100 Hz to 50 kHz frequency range and it is expected that at least two orthogonal components of both the electric and magnetic fields will need to be measured. Crossed 16 meter and 51 meter tip-to-tip booms oriented approximately perpendicular to the local magnetic field shall be provided by the satellite vendor to host the electric field antennas as a conducting component of the boom itself. Wave instrument providers are expected to work closely with the satellite vendors to ensure that the conducting boom system meets the plasma wave measurement requirements. A capability to transmit waves in the frequency range 1- 50 kHz with the intent to stimulate pitch-angle scattering of electrons in the nominal altitude regime of 1.0 - 2.0 Earth radii should be provided. Up to 2 kW of power will be available and it is anticipated that the provider will work closely with the Air Force Research Laboratory to evaluate and implement dynamic tuning circuit technologies to maximize the efficiency of the far-field radiated power. The proposer may combine measurements of various particle types and energy range into single instruments as appropriate; similarly the offeror may combine any plasma wave measurements into single instruments, as appropriate, with the exception of the transmitter and receiver technology which must be proposed as independent items. The offeror shall price the design, manufacture, calibration and integration of any proposed instrument. Costs for on-orbit instrument turn-on and initial calibration, nominally done in the first three months of operations are also required. However, proposed work directed at analysis and archiving of the experimental data is not requested in this PRDA. Project Statement Spacecraft Instrumentation to Measure and Stimulate Space Particles and Plasma Waves in the Medium-Earth Orbit (MEO) Regime 1. BACKGROUND The Air Force Research Laboratory (AFRL) is responsible for the development and execution of the Deployable Structures Experiment (DSX), a suite of four science payloads integrated onto a Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA) ring based three axis stabilized satellite bus nominally slated for launch into a 6000 x 12000 km, 30 degree inclination Medium Earth Orbit (MEO) in the 2007-2008 timeframe with one year required and three year desired operational capability. Scientific research will be conducted with DSX in the areas of (a) the deployment, dynamics, control and MEO environment degradation of large deployable space structures, (b) the performance, radiation tolerance, plasma interactions and annealing of thin film photovoltaics (TFPV) in the MEO environment, (c) the physics of plasma wave injection, propagation, and wave-particle interactions in the magnetosphere as relevant to radiation belt remediation RBR techniques; and (d) the measurement and mapping of energetic particle and plasma distributions in the poorly characterized MEO region. This PRDA seeks proposals of original and innovative research dealing with the development and demonstration of space instrumentation to support both the Space Weather (SWx) and the Radiation Belt Remediation (RBR) payloads on DSX. 2. PROJECT STATEMENT 2.1 Space Weather Specification and Mapping Payload The SWx specification and mapping payload will operate in support of two purposes: to provide particle fluxes and radiation doses to (a) evaluate the performance of the mission's TFPV panels and the its inflatable deployable structures and (b) improve the radiation belt and plasma models in the MEO regime. The TFPV consists of a 10 x 14 foot square panel containing front-side regions of 0.06 inch thick CuInGaSe2 (CIGS) and 0.07 inch thick amorphous silicon with a back-side of 0.08 inch thick plastic material. Energy ranges of interest for panel damage range from 0.1 keV to 10 MeV for protons and 100 eV to 1 MeV for electrons. Deployable structures are nominally constructed of 0.1 inch thick plastic material components deployed at the beginning of the mission and left extended for the duration. A photometry system will measure the position of the tips of the structures and data from the desired space environment instruments will be used to correlate the structure changes to radiation damage. Energy ranges of interest for structure damage ranges from 1 keV to 10 MeV for protons and 0.1 keV to 1 MeV for electrons. To achieve the SWx payload science goals proposers should address the following measurement and modeling objectives. Note that AFRL has already acquired instruments to measure medium energy electrons (20 keV - 1 MeV) and a portion of the medium energy protons (20 keV- 1 Mev). The description of these objective is included for completeness in describing the full payload capabilities. 2.1.1 Electrons - Low energy population (100 eV < E < 50 keV) responsible for effects that include surface charging and damage to TFPV panels. Energy resolution should be 20-30 logarithmically spaced channels. Field-of-view should be sufficient to determine the effect of this population on the TFPV panel with 1 - 5 second time resolution. Pitch-angle resolution is not required. - Medium energy population responsible for effects that include deep dielectric charging (50 keV < E < 1 MeV). Field-of-View should be > 25 degrees (opening half angle) with a sufficient number of differential energy channels to determine the energy deposition to TFPV panels and deployable space structures as well as the shape of the electron flux spectrum between 0.1-1.0 MeV in the nominal MEO orbit regime. Pitch-angle resolution of ten degrees within the field of view is desired. Time resolution of the data should be of the order of 5 to 10 seconds to allow correlation between collected data and spacecraft anomalies. - High energy population (1 MeV < E < 30 MeV) responsible for effects that include damage to internal spacecraft components. This population is not isotropic and should be measured with sufficient angular resolution to image the loss cone and reconstruct the pitch angle distribution with an accuracy of 7 to 12 degrees (opening half angle). Since the DSX spacecraft is not a spinner and the pitch angle measurements must be made using the sensor's field-of-view alone. The sensor must be able to make accurate measurements (less than 10% contamination) in presence of high-energy proton population in the inner belt and during solar particle events. 2.1.2 Protons - Low energy population (100 eV < E < 50 keV) responsible for effects that include damage to TFPV panels. Energy resolution should be 20-30 logarithmically spaced channels. Field-of-view should be sufficient to determine the effect of this population on the TFPV panel, approximately 25 to 50 degrees. Pitch-angle resolution is not required. Time resolution of the data should be of the order of 5 to 10 seconds to allow correlation between collected data and spacecraft anomalies. - Medium energy population (50 keV < E < 10 MeV) responsible for effects that include damage to TFPV panels, deployable structures and lightly shielded spacecraft components. Field-of-View should be > 25 degrees (opening half angle) Sufficient differential energy channels to determine the shape of the proton energy spectra, so that its deposition pattern in the TFPV can be determined. Pitch-angle resolution of ten degrees within the field of view is desired. Time resolution of the data should be of the order of 5 to 10 seconds to allow correlation between collected data and spacecraft anomalies. - High energy proton population (10 MeV < E to 400-500 MeV) responsible for effects that include single event upsets and dose degradation. Knowledge of this population is needed to develop new, improved climatological, specification and forecasting models of high energy protons in the MEO regime. This population is not isotropic and must be measured is sufficient angular resolution to image the loss cone and reconstruct the pitch angle distribution with an accuracy of 7 to 12 degrees (opening half angle). Since the DSX spacecraft is not a spinner and the pitch angle measurements must be made using the sensor's field-of-view alone. The sensor must be able to make accurate measurements (less than 10% contamination) in presence of high-energy electron population in the outer belt and during solar particle events. 2.1.3 Dosimetry Radiation dosimetry measurements are desired behind 0.08 and 0.25 inches of aluminum. The degrader shape may be flat of hemispherical. Field-of view should be close to 180 degrees. Differentiation of the dose due to electrons and protons is desired. 2.1.4 Single Event Effects Single Event Effects are events where a high-energy particle traversing a digital device creates sufficient charge in a cell of the device to change its state, with potentially harmful results. The absolute probability of these events depends on the spectrum of the incident particles and the exact device type. Nevertheless, a relative probability may be obtained without detailed knowledge of all the parameters. A measure of this relative probability is desired. 2.1.5 DC Magnetic Field Three dimensional DC magnetic field measurements (0 to 20 Hz) are needed to reconstruct particle pitch angle distributions. This need requires the measurement of the magnetic field between in the range of 100 to 10,000 nT with a sensitivity of 1 nT and with the field vector accuracy of < 1 degrees at all points in the orbit. If a boom is required the offeror must specify the desired material and length. Boom will be provided by the spacecraft contractor. 2.1.6 Instrument Response Modeling Capabilities to use computer programs to develop and implement models of DSX sensors are desired. The models will be used to extract physical data from the instrument responses in cases where the instrument calibrations prove inadequate or unrealistic. Programs must run on AFRL computers and all software must be delivered to AFRL. 2.2 Radiation Belt Remediation Payload The purpose of the RBR payload is to (a) characterize the inner magnetospheric natural and man-made electromagnetic radiation environment in the 0.1-50 kHz frequency range to include plasma mode structure, (b) determine the efficiency of injecting 1- 50 kHz (hereafter referred to as the Very Low Frequency (VLF) regime) electromagnetic wave power into the inner magnetosphere from a space platform, and (c) demonstrate perturbations on space particle populations due to injected VLF wave power. To achieve these objectives the payload components described below are anticipated. Proposers should structure the proposal in a manner that will allow the selection of individual components. 2.2.1 Electric Field Receiver Measurements should be made of electric fields from 100 Hz to 50 kHz at a sensitivity of approximately 1E-16 V^2/(m^2-Hz) and 16 bit resolution. Two boom structures will be provided with a nominal extensions of 16 meters and 51 meters tip-to-tip orientated orthogonal to the local magnetic field and each other. Though the boom structures will not be the responsibility of the offeror, the proposed effort should include interactions with the boom provider to ensure appropriate widths, conductance, and other relevant properties. The offeror should provide options to employ either or both of the two booms. 2.2.2 Magnetic Field Receiver Measurements should be made of magnetic field components from 100 Hz to 50 kHz at a sensitivity of approximately 1E-11 nt^2/Hz and 16 bit resolution in at least two directions perpendicular to the local magnetic field. An option for a measurement of the component along the direction of the magnetic field is desired. If a boom or booms are required the offeror must specify the desired material and length. Boom(s) will be provided by other payload or spacecraft providers. 2.2.3 Electric Field Transmitter The instrument must be designed to produce electromagnetic radiation capable of causing pitch angle scattering of greater than 100 keV electrons trapped in the inner magnetosphere. A nominal 51 meter tip-to-tip boom structure will be provided orientated orthogonal to the local magnetic field. Though the boom structure will not be the responsibility of the offeror, the proposed effort should included interactions with the boom provider to ensure appropriate widths, conductance, and other relevant properties. On-orbit power will be provided by two systems: (a) a standard 135 W average power (255 W peak) commercial solar panel and (b) the TFPV experimental panel capable of providing 1-2 kW. The transmitter must be able to couple to both power systems and must be designed to optimize far-field radiated power using the 1-2 kW source. Offerors should plan on working closely with AFRL scientists and engineers to evaluate and implement antenna dynamic matching network that will be provided separately from the instrumentation requested in this PRDA. Dynamic tuning circuitry is required to optimize performance as the near-field plasma sheaths and currents change in the course of a wave period. Designs should have the ability to default to standard tuning circuitry. 2.2.4 Loss Cone Electron Detector Knowledge of the loss cone electrons (100 to 500 keV with velocity nearly parallel to the local magnetic field) is needed to understand and quantify the effects of the transmitter on the scattering of the trapped electron population into the loss cone. The field-of-view must be less than 10 degrees since the loss cone angle is about 16 degrees at the DSX altitudes. Expected loss cone fluxes are of the order of 100 to 10,000 electrons / cm^2-sec-sr at E = 300 keV, with E falling off as exp(-E/150) with E in keV. 2.2.5 Local Cold Plasma Density Measurements of in-situ cold plasma density is required which, together with the DC magnetic field measurements, will allow the determination of the local index of refraction. Sounding technique methods which extend the transmitter and receiver frequency ranges will be acceptable provided they are competitive in cost and spacecraft resources with direct sampling techniques. 3. Spacecraft 3.1 Power The spacecraft Power Management and Distribution (PMAD) system will provide appropriate power input to the RBR transmitters. The PMAD system will provide to each transmitter a voltage of 100 Volts DC and a total power of 2 kW. An experimental solar panel will provide the primary input power for the PMAD box with approximately 2.2 kW of power at approximately 100 V DC. Any secondary power necessary to energize the PMAD box will be provided from the spacecraft primary solar array. The specifications are summarized below: PMAD Primary Input Power: < 2.2 kW at ?50 VDC PMAD Secondary Input Power: <10 W at 28 VDC PMAD Output Voltage: 100?8 VDC (2-4 channels) PMAD Output Power: 2.0 kW (total) PMAD Power Conversion Efficiency: >90% 3.2 Attitude and Control and Determination System (ADCS) Type: 3-axis stabilized (desired nominal) for Normal Mode Attitude Control: <2? per axis, 3s Attitude Knowledge: <1? per axis, 3s Orbit Determination Accuracy: ?5 km 3.3 Launch Schedule The nominal launch date is mid 2007. Instrument delivery integration testing at is mid 2006. There is a possibility of a launch delayed to mid 2008, and a corresponding instrument delivery date of mid 2007. Proposers should indicate the effect of the two delivery dates on hardware development and cost. Proposers should include the costs of instrument integration in their cost section of the proposal. 4. Other The instrument shall have an RS-422 data interface, unless specific permission for another interface is granted by AFRL. AFRL desires that the successful offerors provide information that will allow AFLR to track the progress of the work using it project tracking software. BASIS FOR AWARD: Technical proposals will be evaluated using the following factors, of equal importance, based on a peer scientific review. (a) Demonstrated technical and/or scientific merit and its relevancy to current AFRL needs, including capabilities and related experience, facilities, techniques, or unique combinations of these which are an integral factor for achieving proposal objectives, (b) impact of successful development on the performance of space systems and AFRL mission, (c) new or unique ideas which enhance state-of-the-art or scientific knowledge, (d) the qualifications, capabilities, and experience of the proposed principal investigator, team leader, and other key personnel who are critical to achievement of the proposed objectives, (e) feasibility of accomplishing tasks. Cost proposals will be evaluated using the factor of completeness, reasonableness and realism. Technical considerations are more important than cost, although cost will be considered a significant factor. No further evaluation criteria will be used in selecting proposals. Subject to the availability of funds, the Government reserves the right to select for award any, all, part, or none of the proposals received. DELIVERABLES WILL INCLUDE: Scientific/Technical Reports, annually and final R&D Status Reports (quarterly) Contract Funds Status Reports (required if effort >$1M) Hardware: 5-9 Instruments PROPOSAL PREPARATION INSTRUCTIONS: Responses must provide new and unique concepts ideas, or approaches in order to qualify for evaluation and consideration for award. Proposal shall be submitted in two (2) parts: (1) Technical Proposal: The Technical Proposal shall include an Executive Summary, Program Description, Program Plan, Milestone Chart, Facilities and Equipment Description, Description of Relevant Prior Work, Management Plan, and Resume of Key individuals. The technical proposal shall also include a Statement of Work detailing the technical tasks to be accomplished under the proposed effort and be suitable for contract incorporation. The technical proposal shall be limited to fifty (50), (12-pitch or large type) single spaced, double-sided, 8.5x11 inch pages. The page limitation includes all information i.e., covers, indices, photographs, appendices, attachments, resumes, etc... Each printed side counts as one page. (Caution: The Government will not review more than the page limitation). (2) Cost Proposal: There is no page limitation on the Cost Proposal. The Cost Proposal should be valid for no less than 180 days and be broken out by Cost Element and Government fiscal year. The Government encourages submission of innovative and creative proposal to solve any one, all or a combination of the problems discussed herein. Forward six (6) copies of each proposal to ESC/PKR (Attn: John W Flaherty) Bldg, 1520, 3rd Floor, 104 Barksdale St., Hanscom AFB, MA 01731-1806. The Battlespace Environment Division, Space Weather Center of Excellence (AFRL/VSBX) has been assigned overall responsibility for providing the necessary acquisition/technical management of this program. Responses should reference PRDA #AFRL/VSB04-01. QUESTIONS of a TECHNICAL NATURE may be referred to Dr. Bronislaw Dichter, 781-377-3991 email Bronek.Dichter@hanscom.af.mil. CONTRACTUAL and COST QUESTIONS should be referred to the CONTRACTING OFFICER 781-377-2529 email john.Flaherty@hanscom.af.mil Government Estimates: Delivery dates for the instruments are approximately mid 2006 to mid 2007 (see section 3.3) Government estimate in total for these contractual efforts is an award of 5-9 contracts for approximately one hundred (100) man-years, with a period of performance not to exceed sixty (60) months plus three (3) months for final report per efforts. Work is anticipated to begin in the October 2004 time frame. Each contract will be incrementally funded. The cost of preparing a proposal to a PRDA is not considered an allowable direct charge to the resulting contract or any other contract. It is, however, an allowable expense to the normal bid and proposal indirect cost specified in FAR 31.205.18. Proposals received in response to this announcement will be deemed in accordance with the Competition in Contracting Act of 1984. Every effort will be made to protect the confidentially of the proposals. In order that the proposals are afforded proper handling, offerors must mark their proposals with restrictive language stated in FAR 15.509(a). Offerors are cautioned that ONLY GOVERNMENT CONTRACTING OFFICERS are legally authorized to commit the government. Firms responding should indicate if they are qualified as a Small Business, a Socially and Economically Disadvantage Business or a Woman-Owned Business. Offerors are request to provide a name and telephone number of point of contact. Closing date for submission of proposal is 10 May 2004. See Note 26.
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