Response to Requirements
THE PLANETARY SOCIETY
65 North Catalina Avenue
Pasadena, California 91106
Bruce Betts, Ph. D.
Director of Projects
Proposal Submitted
by
xrd1 Consulting
*, Michigan *
xrd1 Proposal No. 2007 – 001
BLOG COPY
August 31, 2007
The Planetary Society
Apophis Asteroid Tagging Mission
TABLE OF CONTENTS
Page No.
Cover Letter 3
Executive Summary 4 - 5
I. Our Understanding of the Situation 6 - 7
II. Objectives of the Project 8
III Technical Section 9
III.1. Phases I – III: Summary 9 - 11
III.2 Phases I – III: Details 12 - 14
IV. Project Results 14 – 17
APPENDIX 18
Error Ellipse Illustrations and Analysis 19
Ephemeris Data 99942 Apophis 20 - 21
Locations/distances VLBA 22
Ketron PEEK Data 23
Proposed Patent Application 24 – 27
Justification Outline 28 - 30
Links to Proposed Suppliers/Equipment 31
Other Links 32 - 37
xrd1 Consulting
August 31, 2007
Dr. Bruce Betts, Director of Projects
The Planetary Society
65 N. Catalina Avenue
Pasadena, CA 91106
Dear Dr. Betts:
xrd1 is proposing a novel “asteroid tagging” method for the Apophis Asteroid project. For the past several months I have been devoting much of my time and energy into the development of this conceptual piece of work/design. The design, as stated in our Notice of Intent (NOI) is a radio interferometer attached to the asteroid with a “tri-tether” system. I also believe that if the plan is successful, it may suitable for deployment on other problem asteroids, near-earth-objects (NEO’s), etc.
xrd1 has only theoretical experience in working with such a system, as we believe nobody has ever attempted anything like this. (Note: We are, however, aware of Space Tethers and the work of Dr. Hoyt and the MAST experiment). We trust we are not competing with Space Tethers or Dr. Hoyt.
As to scheduling, we can only “guesstimate” a theoretical timetable. We only hope the timetable should be sufficient to outlast any potential object-to-earth impact of significance. We are estimating a 1-to-2 year timetable, possibly longer.
xrd1’s proposal for the tri-tether interferometer-tagging project (# 2007-001) is valid for 60 days from the date of this proposal.
We look forward to working with you on the tri-tether interferometer-tagging project.
Sincerely,
EXECUTIVE SUMMARY
INTRODUCTION
After a thorough review of The Planetary Society’s Apophis Mission Design Competition, xrd1 Consulting feels that is has developed one important solution in response to their requirements. This response is our proposed TriTether Radio Interferometer (TTRIF) system for tagging the 99942 Apophis asteroid. If successful in its response and its mission, we would look forward to deploying similar technology to other potentially dangerous bodies.
APPROACH
If approved, to select, specify, purchase, receive, deliver and assemble the technical elements, instruments, materials, facilities and etc. for the construction and assembly of the TTRIF system in three phases.
PROJECT RESULTS
After completion of Phases I and II, we propose to work with The Planetary Society in the design monitoring of the TTRIF and pending launch of the program and the launch of the system. Design monitoring is to include review of a bid (if one is offered) and delivery of supporting documents, materials, and etc. prior to the final project results.
TIME AND COST OVERVIEW
We anticipate meeting the 99942 Apophis Tagging Mission schedule by completing the required work of Phases I and II within a year after receiving any approvals from The Planetary Society and the needed financing. Phase III expected completion is 6 months after the completion of Phase II. It is not known at this time if a source for the financing can or will be found if only an approval is granted.
Our pricing structure is based on standard costs and estimates for each phase of the project. Our fees (consultation, labor, etc.) include support for all design work (on an annual basis), bid specifications and vendor selections until the system is completed. All out-of-pocket expenses incurred by xrd1 Consulting on behalf of the The Planetary Society mission will be billed at actual cost.
The proposal pricing, configurations and terms stated are valid for 60 (sixty) days form the date on the cover of the proposal.
Note: xrd1 Consulting reserves the right to alter configuration with approval of The Planetary Society for purposes of safety and continuous improvement.
xrd1 Consulting
Was founded in 2005 to assist firms and individuals with their application, processing and consulting needs. We have experience with a wide range of industrial systems and concepts.
The design and construction of the proposed TriTether Radio Interferometer system is complex and requires a dedicated, resourceful and inspired supplier. We believe that xrd1 Consulting can and does meet those requirements.
xrd1 Consulting
***, the author of this proposal, founded xrd1 Consulting. Mr. * is a degreed chemist (Bachelor of Science, Chemistry) and has long worked in the chemical compounding industries. Mr. * worked mainly as a chemical formulator in product research and development while in industry. Mr. * has many technical interests outside of chemistry and the chemical industry. For example, Mr. * has recently promoted the idea of using microscopic (or miniature)
RFID (Radio Frequency Identification) chips on currency as a countermeasure technology to prevent counterfeiting. See his blog site “
Homeland Currency Security” (
http://homelandcurrencysecurity.blogspot.com/) and the posting:
Low Cost RFID Labels/”Tapes”/”Tags”/”Devices” (
http://homelandcurrencysecurity.blogspot.com/2006/08/low-cost-rfid-labelstapestagsdevices.html).
http://homelandcurrencysecurity.blogspot.com/The Planetary Society
Apophis Asteroid Tagging Mission
I. OUR UNDERSTANDING OF THE SITUATION
As a result of our examination of the Request for Proposal (and existing literature on the subject), we have developed the following understanding of the Society’s situation:
The Planetary Society is currently concerned with the possibility of an impact with the earth and the
Aten Asteroid 99942 Apophis.
The Planetary Society has put out a competition for a Request for Proposal(s) to investigate/develop/invent ways to
“tag” the
99942 Apophis asteroid.
Such an impact warning must be received prior to
99942 Apophis passing through the space/time “keyhole” (as measured by
NeoDys Ephemerides, to date) to avoid/counter/eliminate/mitigate etc. any possibility of impact of the same with earth or any portion of the body of
99942 Apophis.
The current estimated magnitude of an
Apophis/Earth impact explosion is 1480 Megatons. Such an impact explosion would be more than 14 times greater than the
Tunguska Event, but far less than the
KT event. For more information on the potential for an impact with the
99942 Apophis asteroid (or any NEO), please see the report
Dealing with the Impact Hazard; by Morrison, Harris, Sommer, Chapman and Carusi. Human species extinction seems unlikely in an
Apophis/Earth impact scenario, but could lead to widespread social disruption, severe climate disturbance and large-scale human and animal fatalities.
This technology/device/system etc. may have suitable application for other such potential
Near Earth Object (like
99942 Apophis) impact(s). See also:
NASA – Near Earth Object Program. And the
JPL Small-Body Database Browser.
The Planetary Society requires completion and test of such a system prior to the estimated 2017 event where the body will pass within less than 0.75 AU of the earth.
For justification for government funding, follow-through, expeditions, and etc. the proposed technology/device/system must have an error ellipse of 3 s of 14 kilometers or less.
The “Theory of Operation” for the TriTether Radio Interferometer system is based upon the concept of “Geometric Delay” of a radio signal as outlined in the text, Interferometry and Synthesis in Radio Astronomy, 2nd Edition, A. R. Thompson (
National Radio Astronomy Observatory), J. M. Moran (
Harvard Smithsonian Center for Astrophysics) and G. W. Swenson, Jr. (
University of Illinois at Urbana-Champaign). Published:
J. Wiley & Sons. © 2001
(ISBN: 0-471-25492-4).The Planetary Society
Apophis Asteroid Tagging Mission
However, the concept being offered by xrd1 Consulting reverses the assumptions supplied in the text above. Here, the TriTether
Radio Interferometer system (hence, referred to as the “TTRIF”) is designed to supply a radio interferometer signal generator deployed on the surface of
99942 Apophis. Through the attachment of such a “TTRIF” to the asteroid surface via a system of tethers and anchors, the signal generator and RF unit is designed to supply a 1 Gigahertz (or greater) signal. It is believed that such a signal could be “picked up” and monitored by the radio antennas at any of the
Very Large Array (VLA) sites around the globe AND/OR by the
Very Long Baseline Array. Signal reception and interpretation should supply important approach and position information
of the
99942 Apophis asteroid (and other dangerous
Near Earth Objects) as it makes its approach to Earth from deployment on the surface of the asteroid and beyond. We are now proposing the use (also) of the radio interferometer(s) developed by the people at
“Simple Radio Interferometry”. Long life of the proposed signal is proposed to come from a radioisotope powered battery source. These battery sources are under development now by
BetaBatt and
Qynergy.
We have reviewed the concept, its novelty and its merits with our business associates and we feel that an application for a (U. S.) patent is very well advised. Hence, a proposed (first draft) of a patent application for the TTRIF system appears in the appendix. If anything, we also feel that the proposed patent application adds more depth and explanation of the concept and operation of the proposed device.
Copyright, intellectual property rights and patent rights may be held jointly by xrd1 Consulting and The Planetary Society, if The Planetary Society finds these conditions desirable and if any awards are given to our proposal. If not, full copyright and all other rights are to be retained by xrd1 Consulting. We feel that sharing these rights with The Planetary Society is fair, as the content of the rights would not exist without the design competition promoted by The Planetary Society.
It is proposed that security issues arising from this proposal be handled in the same way. It is not known at this time if secrecy agreements or secrecy clearances will be needed.
No contract or agreement between xrd1 Consulting and The Planetary Society is implied by this proposal or its contents.
The Planetary Society
Apophis Asteroid Tagging Mission
II. OBJECTIVES OF THE PROJECT
The proposed project’s major objectives are divided into three phases.
Phase I
Prepare costs and lists of materials for proposed assembly of the system.
Specifically:
_ Estimated cost(s) in dollars at current
_ Estimated payload (mass) at current
_ Documents for components at current
_ Other decision data as requested (see highlighted links in document)
Instrument/Item
Description
Quantity
$Cost/Estimate
Payload (pounds)
Payload (Kg)
1S1G4A
GHz RF Source
3
18000
55
25
SF 1000
1GHz Signal Generator
3
4500
10
4.55
Dyneema Spool
Tether material
1 spool
10000
5000
2272.73
40 foot Anchor
Tether support
3
3500
3300
1500.00
Betavoltaic Power
Power source
3
50000
500
227.27
Victrex Panels
Shielding
18
26400
100
45.45
Fasteners, etc.
Hardware, Attachments
20000
2000
909.09
Labor, Consultation
6000 hours
180000
Facilities
Rent, Utilities
250000
Computers/Software
Computer Equipment
10000
Patent(s), etc.
Patent
2000
Safety/Equipment/Insurance
Safety
As Needed
Tools/Tool Chest/Kits
Same
As Needed
Shipping/Packaging
Ground Transport
As Needed
Office, Custodial Supplies
Paper, etc.
10000
Sub-Total
584400
10965
4984.09
Instrument/Item
Reference
1S1G4A
AR RF Microwave InstrumentationSF 1000
Signal Forge SF1000Dyneema Spool
DSM - DSM Dyneema - Dyneema® Yarn40 foot Anchor
PricesBetavoltaic Power
BetaBatt, Inc. Victrex Panels
Victrex Peek Plastic SourcePhase II
Prepare technical data for the TTRIF system components.
The Planetary Society
Apophis Asteroid Tagging Mission
Phase III
III. TECHNICAL SECTION
III.1 Phases I – III: Work Plan Summaries
Phase I – System Design Development Requirements
Essential activities are needed to develop the TriTether Radio Interferometer system requirements and to achieve deliverable results. These activities are:
1. Develop program based on current requirements
_ Theory of Operation
The TTRIF system concept is a mission deployable radio interferometer
constructed from a set of three radio signal generators. The radio signal
generators are to be made from a high-frequency microwave source linked
to a high-frequency signal generator. Each signal generator is designed with
its own long-life power supply. The proposed power supply/supplies
are radioisotope batteries – the types of which are currently under
development. Each of these (three) assemblies is attached
by a single tether and anchored to the surface of the intended body after
delivery and “planetfall”. Each signal generator is designed to be tethered.
The tethers are then individually anchored to the surface as a single
“unit” or in an equiangular arrangement. The placement of the anchored/
tethered signal generators is to be done in such a way as to minimize the
“error ellipse” of the TTRIF. The placement of each signal generator is
also planned to be equidistant so as to achieve the geometric delay signal
property necessary to a radio interferometer. The signal generated will
be in the 1 to 2 GHz frequency so as to be “captured” by the VLBA/VLA
or similar antenna arrangement here on Earth or some other suitable antenna.
Timing and strength of signal are to be interpreted as a “warning” to the
asteroid or other body’s approach to the Earth, “keyhole”, etc. Protection of the
signal generator assemblies is to be provided by Victrex PEEK plastic panels in
a standard “box” type construction.
The Planetary Society
Apophis Asteroid Tagging Mission
2. Review hardware and layout/plan of construction
_
Operational effectivenessSpecialized performance of the TTRIF system
Unique performance of the AR
1S1G4A frequency source
Unique performance of the Signal Forge
SF 1000 Signal Generator
Unique performance of the proposed
Dyneema material for the tethers
Unique strength, properties, etc. of
PEEK plastic for meteoroid protection
Long-life, performance of
radioisotope battery/batteries3. Provide decision data:
_ Identify the pros and cons associated with the layout and system approach
Pros:
See Section 2. (above) on the specialized performance of the TTRIF system
and the unique performance of its key technical elements
TTRIF system designed to give unique, “positive” warning signal of approach
TTRIF system designed to “neutralize” geographic effects of asteroid surface
TTRIF system designed so as to give error ellipse of “flexible” accuracy
TTRIF system designed for deployment on extra planetary surface(s)
Cons:
Radioisotope batteries are still under development and may not be commercial
Contingency is to develop alternate power sources (e.g., borrow from NASA, etc.)
Recent deployment failure observed in
MAST program
TTRIF system is untested technology and may require feasibility study
No facilities have been set up for building of the TTRIF
The Planetary Society
Apophis Asteroid Tagging Mission
4. Prepare model of the technical elements of the system
5. Meet and/or consult with The Planetary Society and its representatives as needed.
Phase II – Tri-Tethered Radio Interferometer System Detailed Requirements
Develop work products required by The Planetary Society’s program for an “Asteroid Tagging” System. This will include:
1. Prepare Phase II work products including details of:
_ Signal Generation
A 1 GHz (or greater)
Radio Frequency Signal Generator,
Coupled with a 1 GHz (or greater)
Radio Frequency Amplifier_ Tether System
Primarily made of
UMWPE (Ultra High Molecular Weight Polyethylene) Yarn_ Geometric Delay of the Signal
Where simple geometric delayTg = (D/c)sinq where the wavefront originates from angle q, D is the separation distance between receiver sites (from: Interferometry and Synthesis in Radio Astronomy, 2nd Edition, A. R. Thompson (
National Radio Astronomy Observatory), J. M. Moran (
Harvard Smithsonian Center for Astrophysics) and G. W. Swenson, Jr. (
University of Illinois at Urbana-Champaign). Published:
J. Wiley & Sons. © 2001
. ISBN: 0-471-25492-4)
The Planetary Society
Apophis Asteroid Tagging Mission
_
Battery Power SourceA radioisotope battery source was originally proposed for the TTRIF project so as to meet with any expected delays/”windows”, etc. between now and the 2017, 2029, 2036, etc. 99942 Apophis approach events. It is believed that the proposed battery power of the source(s) will supply up to 1 Watt per battery – which should be sufficient power for the signal generator(s) and the amplifier(s). A power converter(s) may also be needed to complete the design. (Note: The
National Science Foundation has awarded a grant to the proposed supplier. See:
Award Abstract #0320029)
_ Launch Time “Window”
(We can only estimate a “window” of 2+ to 30+ years at this time – authority must come from agency/agencies responsible for space launch and deployment)
_
VLBA Signal Reception
The TTRIF system concept has been designed with a 1 GHz to 1.5 GHz reception in mind for its proposed “warning signal”
_
Transmitter Protection_
Tether Anchor_ (Interpretation of) Received Warning Signal
Again, the TTRIF system concept has been designed to transmit its proposed “warning signal” to locations of the VLBA
2. Review all work products with The Planetary Society.
3. Present to The Planetary Society.
Phase III – Design Monitoring
The activities in this phase will include:
1. Review bid package and supporting technical documents and specifications for conformance to project scope.
2. Provide comments and present to The Planetary Society.
3. Review proposed Planetary Society modifications to the design requirements resulting from hardware and technology changes and the like and coordinate these changes with The Planetary Society.
III.2 Phases I – III: Work Plan Details
Phase I – TriTether Radio Interferometer Design Development Requirements
Other Planning Information
Define Planned Work Flows
The Planetary Society
Apophis Asteroid Tagging Mission
Develop planned workflow throughout the Facility
_ Office area(s)
_ Computer support
_ Design Lab/Assembly Area
Develop Initial Program Estimates
Review the assumptions used to arrive at the planned material estimate and evaluate design requirements in light of those assumptions.
Develop projections of system requirements based upon:
_ Expected effects of mission/technology on future missions
_ Equipment dimensions for hardware
Develop Decision Data
Develop decision data for selecting the methods for providing protection and/or shielding to the TriTether
Radio Interferometer system
_ Shielding of Signal Generator(s)
_ Cost of protection
_ Potential Risks
Identify Strategic Decision Issues for the TTRIF
On the basis of the information obtained, we will identify strategic decisions that The Planetary Society, must make prior to completing the TTRIF design and construction including facilities for assembly of the same.
· No facility for the design and building of the (TriTether Radio Interferometer) system exists at this time
· Suggestions to locations, facilities, etc. for the facility/facilities
· Level of flexibility to accommodate location, business and technical changes
· Location of operations
· Redundancy (if any)
· Level of battery power and availability of same
· Other
In addition, we expect other issues may arise from our data-gathering efforts. For each issue we will research and articulate alternatives and their pros and cons for consideration by The Planetary Society.
2. Present Alternatives for Decision Making
We will present written and oral materials describing alternatives to facilitate the decision-making process for The Planetary Society, if any can be found to exist.
Error Ellipse Estimate
_ We currently estimate a 3s of .38 kilometers based on the current proposed tether length of 50 meters per tether (total of three, laid out in a roughly triangular area on
The Planetary Society
Apophis Asteroid Tagging Mission
99942 Apophis). Better estimates are not available at this time due to the untested status of this technology. See page 19 (the appendix) of the proposal for our current error ellipse estimate of 3sigma of .38 kilometers.
Precision and Accuracy
_Precision and accuracy of the measurement technique of radio interferometry is well known throughout the literature and is believed to give the highest possible precision measurements. For example, see the article
Precision estimates of universal time from radio-interferometric observations.
Contingency
_ xrd1 Consulting is prepared to cede/turn over/license or otherwise to any over the design, research, engineering and etc. of this project to an appropriate, licensed
engineering firm if all parties find it is the best interests of the Apophis Tagging Mission to do so.
3. The Planetary Society Communicates Its Decisions
If The Planetary Society makes any decisions on the project and/or the TTRIF and communicates them to xrd1 Consulting, we will incorporate those decisions into the remaining design requirements to the best of our abilities.
4. Complete the Phase I Work Products
a. Complete facilities requirements (if any) – including safety installations
b. Hire required labor (if available)
c. Purchase required computers/systems, etc. for facilities
d. Purchase/receive components/hardware/software ... for assembly of TriTether
Radio Interferometer system
e. Assemble components of the TTRIF to “pre-shipment” stage for staging at mission delivery location and launch site(s)
IV. PROJECT RESULTS
Phase I
1. Cost(s) in dollars of the facilities for assembly, construction, “pre-staging”, packaging, operations and other unplanned work(s) for the TTRIF system.
2. Cost(s) in dollars of the components and assembly of the TTRIF system.
The Planetary Society
Apophis Asteroid Tagging Mission
3. Cost(s) in dollars of any testing of the TTRIF system.
4. Cost(s) in dollars of any packaging and shipping for the TTRIF system.
5. Additional unplanned cost(s) in dollars for the project.
6. (Estimated) Payload(s) in pounds/kilograms of the TTRIF system and components.
7. Best estimate for cost of planning and “launch” of a feasibility study, if desired.
8. In points (1) through (7) above, the method of reporting and communication is open to verbal, telephone, teleconferencing, written report(s), email and any other mode of communication deemed proper. The Planetary Society, if needed, will communicate back any needed adjustments, revisions and so on to any or all of the above.
Phase II
1. Assemble, print, collate all technical data of the components (dimensions...)
2. Gather facility information (pending funding approval)
3. Again, the method of reporting and communication is open to verbal, telephone, teleconferencing, written report(s), email and any other mode of communication deemed proper. The Planetary Society, if needed, will communicate back any needed adjustments, revisions and so on to any or all of the above.
Phase III
Upon approval, funding and launch of the TTRIF system:
1. Will locate and lease or rent or otherwise facilities for development and assembly of the TTRIF system, if at all possible. Search results to be communicated by us to The Planetary Society.
2. Will begin purchasing procedures and processes to obtain equipment components outlined for the TTRIF system. Purchasing documents, orders, processes and procedures to be reviewed with The Planetary Society.
3. Will begin selection and hiring procedures for engineering personnel for the TTRIF system. Selection and hiring process to reviewed and approved by The Planetary Society.
The Planetary Society
Apophis Asteroid Tagging Mission
4. Purchase /rent/lease office equipment for the maintenance and operation of the facility site and building. Selection of said equipment to be reviewed and approved by The Planetary Society.
5. Or: look at other licensed engineering firms or other for purposes of accomplishing the same. Review and authorization to be reviewed and approved by The Planetary Society.
6. Develop construction prints and/or plans for assembly, in-house “testing” of the TTRIF. All of which are to reviewed and approved by The Planetary Society.
7. Assemble/build/construct the TTRIF system at the established facility. Oversight and approval to be conducted by The Planetary Society.
8. Review and test power and signal generation of the TTRIF system. Report results to The Planetary Society.
9. “Stage” and package the TTRIF for shipment to the launch facility. Review and approval to be conducted by The Planetary Society.
10. Work with a/the launch facility for receipt of the TTRIF system and coordinate any further needed assembly. Oversight and approval to be conducted by The Planetary Society.
11. In points (1) through (10) above, the method of reporting and communication is open to verbal, telephone, teleconferencing, written report(s), email and any other mode of communication deemed proper. The Planetary Society, if needed, will communicate back any needed adjustments, revisions and so on to any or all of the above.
Launch
xrd1 Consulting has some suggested options for launch/deployment of the TTRIF system:
1. Visit the site(s) regarding the NEAR-Shoemaker satellite and its successful “touchdown” on the
Eros asteroid (
http://en.wikipedia.org/wiki/Eros_(asteroid)):
NEAR-Shoemaker became the first spacecraft to land on an asteroid(
http://apod.nasa.gov/apod/ap010213.html).
2. Visit the NEAR-Shoemaker site:
Discovery is NEAR (
http://near.jhuapl.edu/).
3. A
space tug (
Orbital Recovery Gives Go-ahead for its ConeXpress Space Tug; Production to Start in September, First Launch Planned in 2007).
The Planetary Society
Apophis Asteroid Tagging Mission
4. See also
First Space Tug Set to Launch in 2007 (
http://www.newscientist.com/article.ns?id=dn4992).
Post-Launch
It is not known if xrd1 Consulting will be allowed to participate in the post-launch activities of the TTRIF, but we would certainly like to be involved.
Suggestions for participation in the post-launch and deployment activities:
1. Visit and review the proposed launch facility and equipment with The Planetary Society.
2. Be present and/or involved with the physical space launch of the TTRIF system.
3. Communicate with the launch facilities on the success of the launch and deployment of the TTRIF system. Communicate and report with The Planetary Society (and any other organizations or governmental bodies as needed) in an acceptable format.
4. Communicate with launch facilities and radio telescope facilities on signal generation, identification, wave and “fringe” pattern and success or failure of reception of the same.
5. The method of reporting and communication is open to verbal, telephone, teleconferencing, written report(s), email and any other mode of communication deemed proper. Again, The Planetary Society, if needed, will communicate back any needed adjustments, revisions and so on to any or all of the above.
Beyond Post-Launch
We and our business associates have suggested that the science and technology of the proposed TTRIF system may well have other significant applications. xrd1 Consulting wishes to remain intimately involved in the business, science and technology of these other applications.
These applications include but may not be limited to the following:
1. Application to other potentially dangerous near earth objects.
2. Military and defense applications.
3. Studies of other bodies in the solar system (such as the Sun, the Moon and beyond).
4. Other unforeseeable solar system phenomena.
APPENDIX
Uncertainty/
“Error”
Estimate of
Apophis Orbit
Reference:
Image:2004mn4d5 s.gif - Wikipedia, the free encyclopediaSuggested equiangular
spacing of TTRIF
generators and
amplifiers
(“top view”)
Apophis at “extreme” point
10000 km radius
ILLUSTRATIONS AND ANALYSIS OF “ERROR ELLIPSE” ESTIMATE Enlarged View of Apophis
Approximately
45 meters
Approximately
50 meters
Side View of Apophis
Suggested spacing
(approximate) of TTRIF
generators and
amplifiers
(“side view”)
Suggested Analysis and Calculations for “Error Ellipse” of the TTRIF
Spacing
Error ellipse
Properties
(meters)
radii (meters)
e
focus
circumference
area
42.54518
127.6355287
0.866025
18.4226
105.6672021
710.8215
21.27259
63.81776434
standard deviation
45.12597
The Planetary Society
Apophis Asteroid Tagging Mission
From
NeoDys Object List Ephemeridesalculator at
http://newton.dm.unipi.it/cgi-bin/neodys/neoibo?objects:Apophis;ephpred
Equatorial coordinates App. motion Date Hour RA DEC Mag Elong Phase Glat R Delta RA*cosDE DEC Sky plane error (UTC) h m s d ' " (deg) (deg) (deg) (AU) (AU) "/min "/min Err1 Err2 PA 17 Feb 2017 0.000 21 50 33.338 -11 43 18.59 20.1 2.8 3.6 -45.0 0.7471 1.7326 3.0610 1.0367 0.394" 0.007" 72.1 18 Feb 2017 0.000 21 55 33.042 -11 18 16.44 20.1 2.5 3.3 -45.9 0.7467 1.7328 3.0572 1.0495 0.394" 0.007" 71.8 19 Feb 2017 0.000 22 0 31.928 -10 52 56.27 20.1 2.2 3.0 -46.8 0.7464 1.7331 3.0532 1.0617 0.395" 0.007" 71.6 20 Feb 2017 0.000 22 5 29.991 -10 27 19.00 20.1 2.0 2.6 -47.6 0.7461 1.7335 3.0491 1.0733 0.395" 0.007" 71.5 21 Feb 2017 0.000 22 10 27.227 -10 1 25.56 20.0 1.8 2.3 -48.5 0.7460 1.7339 3.0447 1.0842 0.396" 0.007" 71.3 22 Feb 2017 0.000 22 15 23.631 - 9 35 16.88 20.0 1.5 2.0 -49.3 0.7459 1.7343 3.0402 1.0944 0.396" 0.007" 71.1 23 Feb 2017 0.000 22 20 19.201 - 9 8 53.88 20.0 1.3 1.8 -50.1 0.7460 1.7348 3.0354 1.1041 0.396" 0.008" 70.9 24 Feb 2017 0.000 22 25 13.937 - 8 42 17.50 20.0 1.2 1.6 -50.9 0.7461 1.7353 3.0305 1.1130 0.396" 0.008" 70.8 25 Feb 2017 0.000 22 30 7.838 - 8 15 28.70 20.0 1.1 1.4 -51.7 0.7464 1.7359 3.0254 1.1213 0.396" 0.008" 70.6 26 Feb 2017 0.000 22 35 0.904 - 7 48 28.41 20.0 -1.0 1.4 -52.4 0.7468 1.7365 3.0202 1.1290 0.397" 0.008" 70.5 27 Feb 2017 0.000 22 39 53.137 - 7 21 17.59 20.0 -1.1 1.4 -53.1 0.7472 1.7372 3.0148 1.1359 0.397" 0.008" 70.4 28 Feb 2017 0.000 22 44 44.540 - 6 53 57.17 20.0 -1.2 1.6 -53.8 0.7478 1.7379 3.0092 1.1423 0.396" 0.008" 70.2 1 Mar 2017 0.000 22 49 35.116 - 6 26 28.11 20.0 -1.3 1.8 -54.5 0.7485 1.7387 3.0035 1.1480 0.396" 0.009" 70.1 2 Mar 2017 0.000 22 54 24.870 - 5 58 51.36 20.0 -1.5 2.1 -55.1 0.7492 1.7395 2.9976 1.1530 0.396" 0.009" 70.0 3 Mar 2017 0.000 22 59 13.807 - 5 31 7.84 20.1 -1.8 2.3 -55.7 0.7501 1.7403 2.9916 1.1573 0.396" 0.009" 70.0
4 Mar 2017
26 Dec 2017 0.000 19 12 10.373 -20 54 29.65 20.6 -12.8 16.6 -13.8 0.7596 1.6872 3.1264 0.3716 0.397" 0.004" 83.2 27 Dec 2017 0.000 19 17 31.733 -20 45 15.65 20.6 -13.0 17.0 -14.9 0.7581 1.6834 3.1306 0.3977 0.399" 0.005" 82.8 28 Dec 2017 0.000 19 22 53.162 -20 35 24.15 20.6 -13.2 17.3 -15.9 0.7566 1.6796 3.1343 0.4237 0.400" 0.005" 82.4 29 Dec 2017 0.000 19 28 14.593 -20 24 55.37 20.7 -13.5 17.7 -17.0 0.7552 1.6758 3.1376 0.4495 0.402" 0.005" 81.9 30 Dec 2017 0.000 19 33 35.963 -20 13 49.57 20.7 -13.7 18.1 -18.1 0.7539 1.6721 3.1404 0.4751 0.403" 0.005" 81.5 31 Dec 2017 0.000 19 38 57.209 -20 2 7.04 20.7 -14.0 18.4 -19.2 0.7527 1.6684 3.1428 0.5005 0.404" 0.005" 81.1
From NeoDys Object List Ephemerides Calculator at
http://newton.dm.unipi.it/cgi-bin/neodys/neoibo?objects:Apophis;ephpred
Equatorial coordinates App. motion Date Hour RA DEC Mag Elong Phase Glat R Delta RA*cosDE DEC Sky plane error
(UTC) h m s d ' " (deg) (deg) (deg) (AU) (AU) "/min "/min Err1 Err2 PA =========== ====== ============= ============ ===== ===== ===== ===== ======= ======= ======== ======== ======== ======== ===== 27 Feb 2017 0.000 22 39 53.137 - 7 21 17.59 20.0 -1.1 1.4 -53.1 0.7472 1.7372 3.0148 1.1359 0.397" 0.008" 70.4 27 Feb 2017 1.000 22 40 5.295 - 7 20 9.42 20.0 -1.1 1.4 -53.2 0.7472 1.7372 3.0145 1.1362 0.397" 0.008" 70.4 27 Feb 2017 2.000 22 40 17.452 - 7 19 1.24 20.0 -1.1 1.5 -53.2 0.7473 1.7372 3.0143 1.1365 0.397" 0.008" 70.4 27 Feb 2017 3.000 22 40 29.608 - 7 17 53.04 20.0 -1.1 1.5 -53.2 0.7473 1.7373 3.0141 1.1368 0.397" 0.008" 70.4 27 Feb 2017 4.000 22 40 41.762 - 7 16 44.82 20.0 -1.1 1.5 -53.2 0.7473 1.7373 3.0138 1.1370 0.397" 0.008" 70.3 27 Feb 2017 5.000 22 40 53.914 - 7 15 36.59 20.0 -1.1 1.5 -53.3 0.7473 1.7373 3.0136 1.1373 0.397" 0.008" 70.3 27 Feb 2017 6.000 22 41 6.066 - 7 14 28.35 20.0 -1.1 1.5 -53.3 0.7474 1.7374 3.0134 1.1376 0.397" 0.008" 70.3 27 Feb 2017 7.000 22 41 18.215 - 7 13 20.08 20.0 -1.1 1.5 -53.3 0.7474 1.7374 3.0132 1.1379 0.397" 0.008" 70.3 27 Feb 2017 8.000 22 41 30.363 - 7 12 11.80 20.0 -1.1 1.5 -53.4 0.7474 1.7374 3.0129 1.1381 0.397" 0.008" 70.3 27 Feb 2017 9.000 22 41 42.510 - 7 11 3.50 20.0 -1.1 1.5 -53.4 0.7474 1.7374 3.0127 1.1384 0.397" 0.008" 70.3 27 Feb 2017 10.000 22 41 54.656 - 7 9 55.19 20.0 -1.1 1.5 -53.4 0.7475 1.7375 3.0125 1.1387 0.397" 0.008" 70.3 27 Feb 2017 11.000 22 42 6.800 - 7 8 46.86 20.0 -1.1 1.5 -53.4 0.7475 1.7375 3.0122 1.1389 0.397" 0.008" 70.3 27 Feb 2017 12.000 22 42 18.942 - 7 7 38.52 20.0 -1.1 1.5 -53.5 0.7475 1.7375 3.0120 1.1392 0.397" 0.008" 70.3 27 Feb 2017 13.000 22 42 31.083 - 7 6 30.16 20.0 -1.1 1.5 -53.5 0.7475 1.7376 3.0118 1.1395 0.397" 0.008" 70.3 27 Feb 2017 14.000 22 42 43.223 - 7 5 21.78 20.0 -1.1 1.5 -53.5 0.7475 1.7376 3.0115 1.1397 0.397" 0.008" 70.3 27 Feb 2017 15.000 22 42 55.361 - 7 4 13.39 20.0 -1.1 1.5 -53.6 0.7476 1.7376 3.0113 1.1400 0.397" 0.008" 70.3 27 Feb 2017 16.000 22 43 7.498 - 7 3 4.98 20.0 -1.1 1.5 -53.6 0.7476 1.7377 3.0111 1.1402 0.397" 0.008" 70.3 27 Feb 2017 17.000 22 43 19.633 - 7 1 56.56 20.0 -1.2 1.5 -53.6 0.7476 1.7377 3.0108 1.1405 0.397" 0.008" 70.3 27 Feb 2017 18.000 22 43 31.767 - 7 0 48.12 20.0 -1.2 1.5 -53.6 0.7476 1.7377 3.0106 1.1408 0.397" 0.008" 70.3 27 Feb 2017 19.000 22 43 43.899 - 6 59 39.67 20.0 -1.2 1.6 -53.7 0.7477 1.7377 3.0104 1.1410 0.397" 0.008" 70.3 27 Feb 2017 20.000 22 43 56.030 - 6 58 31.20 20.0 -1.2 1.6 -53.7 0.7477 1.7378 3.0101 1.1413 0.397" 0.008" 70.3 27 Feb 2017 21.000 22 44 8.160 - 6 57 22.72 20.0 -1.2 1.6 -53.7 0.7477 1.7378 3.0099 1.1415 0.397" 0.008" 70.3 27 Feb 2017 22.000 22 44 20.288 - 6 56 14.22 20.0 -1.2 1.6 -53.8 0.7477 1.7378 3.0097 1.1418 0.397" 0.008" 70.3 27 Feb 2017 23.000 22 44 32.415 - 6 55 5.70 20.0 -1.2 1.6 -53.8 0.7478 1.7379 3.0094 1.1420 0.396" 0.008" 70.3 28 Feb 2017 0.000 22 44 44.540 - 6 53 57.17 20.0 -1.2 1.6 -53.8 0.7478 1.7379 3.0092 1.1423 0.396" 0.008" 70.2
The VLBA radio telescopes are located at:
Mauna Kea,
Hawaii (
19°48′04.97″N, 155°27′19.81″W)
Owens Valley,
California (
37°13′53.95″N, 118°16′37.37″W)
Kitt Peak,
Arizona (
31°57′22.70″N, 111°36′44.72″W)
Pie Town,
New Mexico (
34°18′03.61″N, 108°07′09.06″W)
Los Alamos, New Mexico (
35°46′30.45″N, 106°14′44.15″W)
Fort Davis, Texas (
30°38′06.11″N, 103°56′41.34″W)
Brewster, Washington (
48°07′52.42″N, 119°40′59.80″W)
North Liberty, Iowa (
41°46′17.13″N, 91°34′26.88″W)
Hancock, New Hampshire (
42°56′00.99″N, 71°59′11.69″W)
St. Croix,
United States Virgin Islands (
17°45′23.68″N, 64°35′01.07″W)
Approximate Relative Distances of the VLBA Antennas:
Start
Coordinates (start)
End
Coordinates (end)
Approx. Distance
Owens Valley, CA
37°13′53.95″N, 118°16′37.37″WKitt Peak, AZ
31°57′22.70″N, 111°36′44.72″W707 miles
Kitt Peak, AZ
31°57′22.70″N, 111°36′44.72″WPie Town, NM
34°18′03.61″N, 108°07′09.06″W358 miles
Pie Town, NM
34°18′03.61″N, 108°07′09.06″WLos Alamos, NM
35°46′30.45″N, 106°14′44.15″W259 miles
Los Alamos, NM
35°46′30.45″N, 106°14′44.15″WFort Davis, TX
30°38′06.11″N, 103°56′41.34″W572 miles
Fort Davis, TX
30°38′06.11″N, 103°56′41.34″WBrewster, WA
48°07′52.42″N, 119°40′59.80″W1883 miles
Brewster, WA
48°07′52.42″N, 119°40′59.80″WNorth Liberty, IA
41°46′17.13″N, 91°34′26.88″W1761 miles
North Liberty, IA
41°46′17.13″N, 91°34′26.88″WHancock, NH
42°56′00.99″N, 71°59′11.69″W1141 miles
Owens Valley, CA
37°13′53.95″N, 118°16′37.37″WHancock, NH
42°56′00.99″N, 71°59′11.69″W2841 miles
Hancock, NH
42°56′00.99″N, 71°59′11.69″WKitt Peak, AZ
31°57′22.70″N, 111°36′44.72″W2671 miles
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Application for U. S. Patent (Proposed)
Abstract
The TTRIF (TriTether
Radio Interferometer) system concept is a mission deployable radio interferometer constructed from a set of three radio signal generators.
The radio signal generators are to be made from a high-frequency microwave source linked to a high-frequency signal generator. Each signal generator is designed with its own long-life power supply. The proposed power supply/supplies are radioisotope batteries – the types of which are currently under
development. Each of these (three) assemblies is attached
by a single tether and anchored to the surface of the intended body after
delivery and “planetfall”. Each signal generator is designed to be tethered.
The tethers are then individually anchored to the surface as a single
“unit” or in an equiangular arrangement. The placement of the anchored/
tethered signal generators is to be done in such a way as to minimize the
“error ellipse” of the TTRIF. The placement of each signal generator is
also planned to be equidistant so as to achieve the geometric delay signal
property necessary to a radio interferometer. The signal generated will
be in the 1 to 2 GHz frequency so as to be “captured” by the VLBA/VLA
or similar antenna arrangement here on Earth or some other suitable antenna.
Timing and strength of signal are to be interpreted as a “warning” to the
asteroid or other body’s approach to the Earth, “keyhole”, etc. Protection of the
signal generator assemblies is to be provided by Victrex PEEK plastic panels in
a standard “box” type construction.
Inventors: ***(*, Michigan)
Assignee: xrd1 Consulting (*, Michigan) and
The Planetary Society (Pasadena, California)
Claims What is claimed is:
1) A mission-deployable TTRIF (TriTether
Radio Interferometer) system for application to dangerous Near Earth Objects and other planetary bodies constructed from;
a) One to three 1 Gigahertz (or higher frequency) frequency radio/microwave amplifier,
b) One to three 1 Gigahertz (or higher frequency) signal generator,
c) One to three tethers,
d) One to three anchors,
e) One to three radioisotope batteries (or some suitable power source) and
f) One to three protective cases (or “boxes”) constructed of high-strength plastic.
2) A mission-deployable TTRIF (TriTether
Radio Interferometer) system wherein the individual components of Claim 1 are assembled to provide;
a) One to Three Gigahertz (or higher frequency) frequency interferometer signal(s) suitable for detection for antennas such as those at the
VLA/VLBA or
“Simple Radio Interferometry”,
b) Having been suspended by an equidistant and/or equiangular system of tethers and anchors,
c) Power supplied by
radioisotope batteries (or some other suitable power source, such as those under development at
BetaBatt and
Qynergy),
d) Protection provided against meteoroid impacts, etc. by
PEEK (
Polyetheretherketone plastic) cases (or “boxes”) constructed from same (such as “
Victrex” supplied by
Modern Plastics),
e) Signal generation to be supplied by a signal generator (e.g. such as the
SF 1000 or
SF 1000E supplied by
Signal Forge Corporation),
f) Frequency generation to be supplied by a radio/microwave amplifier (e.g. such as the
1S1G4A supplied by
ar Worldwide Corporation),
g) Tethers to be constructed of
Ultra High Molecular Weight Polyethylene (e.g. “
UHMWPE” such as “
Dyneema Yarn” supplied by
DSM),
h) And anchored by 40 foot anchors (or some suitable device, such as supplied by
Para-Tech or
Fortress).
Description FIELD OF THE INVENTION
The present invention relates to
radio interferometry. More particularly, it relates to the application of a system (three) radio signal generators to create a “fringe wave pattern” to specifically identify position and distance of
a dangerous planetary body (e.g.
99942 Apophis, etc.)
BACKGROUND OF THE INVENTION
This year,
The Planetary Society has issued an
RFP (Request for Proposals) for its
Apophis Tagging Mission Design Competition. As nothing like “tagging” an asteroid has ever been done before, the author of this patent application came up with his own proposed design system concept and submitted an
NOI (Notice of Intent) to
The Planetary Society. The design system concept that the author came up with was the idea of an asteroid-based
radio interferometer which signal would be of sufficient frequency (say 1 GHz or higher) that could be detected/monitored etc. by an antenna or array of antennas (like the
VLA or the
VLBA or other) on the earth. The signal generated by the interferometer would provide a “warning signal” and possibly a “critical track” of the
99942 Apophis asteroid during its close-approach events scheduled for
2017, 2026, 2039 and so on. The design is intended to also have application to other
dangerous planetary bodies near the Earth. The tethering concept of the design was developed to overcome or “neutralize” geographic effects on the asteroid surface. The tether concept also supplies the needed
geometric delay property necessary to a
radio interferometer.
SUMMARY OF THE INVENTION
It is an object of the present invention to disclose tethered
radio interferometer systems and technology for the purpose of providing location, approach and warning information and signal(s) of
dangerous near earth bodies (e.g.;
99942 Apophis). The invention disclosed herein is the aforementioned TTRIF (TriTether Radio Interferometer).
The construction of the present invention comprises the following components:
(a) a 1 to 2 GHz (Gigahertz) signal generator(s),
(b) a 1 to 2 GHz (Gigahertz) radio amplifier(s),
(c) a tether or combination of tethers,
(d) a
radioisotope battery or other suitable power source,
(e) an anchor or system of anchoring devices,
(f) and one to three protective “boxes” or “cases”.
The construction of the present invention should give the following desirable properties:
(a) a precise location of a/the dangerous planetary body,
(b) a high frequency radio signal(s) capable of being detected by the
VLBA,
VLA or some other suitable antenna or array of antennas,
(c) a “fringe pattern” interferometer signal(s),
(d) a geometric delay pattern of the signal(s),
(e) a “24/7” signal (that is continuous operation and detection),
(f) a “flexible” error ellipse below or at 3sigma of 14 kilometers,
(g) a long life power source to maintain radio signal lifetime,
(h) protection of the signal generating equipment,
(i) attaching/anchoring of the signal generating equipment to the planetary body,
(j) an estimated payload of approximately 11,000 pounds (or 5000 kilograms),
(k) and deployable via shuttle, rocket, etc. or some other transport to the surface of the planetary body.
DESCRIPTION OF THE PREFERRED CONSTRUCTION
The preferred TTRIF (TriTether Radio Interferometer) is constructed from the following components; one or more 1 GHz (or higher) radio signal generator, one or more 1 GHz (or higher) radio signal amplifier, one or more protective plastic “boxes” or “cases”, one or more
radioisotope batteries (or some suitable power source), one or more tethers or tether systems, and one or more anchors or anchoring devices.
The preferred signal generator component is the
SF 1000 (or
SF 1000E) available from the
Signal Forge Corporation.
The preferred radio amplifier is the
1S1G4A available from
ar Worldwide Corporation.
The preferred tether material is
Dyneema Yarn (
Ultra High Molecular Weight Polyethylene or
UHMWPE) available from the
DSM Corporation. The material (
UHMWPE) is also notable for its
tensile and creep properties.
The preferred
anchor is available from
Para-Tech Corporation.
The preferred plastic casing material is
“Victrex” (
PEEK) and is available (in sheet form) from
Modern Plastics Corporation.
Tensile strength of the material is typically 90
MPa.
Young’s Modulus of the material is typically 3700
MPa. The preferred material (
PEEK) is also notable for its ability to withstand pressures typically experienced in
ultra high vacuum.
The preferred
radioisotope battery is currently under development by
BetaBatt and
Qynergy.
EXAMPLE
No physical examples of the construction are present at this time.
The Planetary Society
Apophis Asteroid Tagging Mission
TriTether Radio Interferometer Justification
Date of Status: August 31, 2007
(Note: This Justification Outline was developed based on information provided on the
Information Services Board website).
I. Executive Summary
xrd1 Consulting in response to The Planetary Society’s Request for Proposals has developed its approach to the “tagging” mission proposed for the 99942 Apophis Aten asteroid. The approach/concept of this development is to design/construct a TriTether Radio Interferometer (herein referred to as “TTRIF”) for signal generation upon touchdown upon the surface of 99942 Apophis. If a successful warning signal can be generated/received, the technology may be suitable for application to other dangerous and potentially dangerous Near Earth Objects. “Touchdown” of the TTRIF seems feasible based on the satellite touchdown achieved on the Eros asteroid. A current high cost estimate of the project prior to any “liftoff” (to be supplied another agency) is about $ 600,000 US. See the body of our proposal for more information.
II. Background and Needs Assessment
· Business environment
_See
NASA’s
Near Earth Object Program_See
Tethers Unlimited website_See
Young Engineer’s Satellite 2 Project· Business needs
_See
Apophis Mission Design Competition· Business opportunities
_Development of new dangerous asteroid warning system(s)
_Development of new near earth body signal generation for identification
_Mitigation of potential asteroid impact disaster scenario/situation(s)
· Business service goals
_To provide a new and working technology for the warning system and other aerospace related applications
· Statutory requirements
_ See
Public Law No. 109-155· Other
_Potential for human disaster avoidance
_Potential patentable technology
III. Objectives
· Problems to be solved
_Routine, “positive” warning signal of potential impact(s) with planetary bodies
· Expected tangible and intangible benefits
_ Disaster avoidance and/or mitigation
_ Cost control of same
_Humanitarian aspect/mission of warning signal tagging of planetary bodies through application of same
· Service/delivery customer satisfaction enhancements
_Develop and/or increase confidence interval in asteroid impact warning
_Improve planetary body survey rate > 90% (see
Near Earth Object Program)
· Response to statutory requirements
· _Compliance
Sec. 101 (RESPONSIBILITES, POLICIES & PLANS) (2) (B) (i) & (2) (B)· Other
_Application of the technology to other potentially catastrophic events (e.g., potential impacts with other planetary bodies…) over the short- and long-term
IV. Organizational Impacts (as applicable)
· Inter-agency
_
NASA· Intra-agency
_
Jet Propulsion Laboratory· Program(s)
_
Near Earth Object Program_
Very Long Baseline Array· Sub-program(s)
_
Spaceguard· Customers of agency activities
_
The Planetary Society· Other
_
United States Patent Office_Canadian Space Agency
_European Space Agency
_Japan Space Agency
V. Process/Procedural Impacts (as applicable)
· Impact on work progress
_To be determined
· Training needs
_See
Aerospace and Defense Benchmarking· Job content
_Mechanical assembly (e.g., fastening, welding...)
_Packaging (shipping, transport...)
_Engineering (radio, mechanical, electrical, software, hardware...)
_Custodial
_Office, clerical, data entry
_Communication (reporting, scientific, engineering, customer support…)
_Purchasing, accounting (payables, billables…)
· Impact on organizational structure
_Maximum
· Other
_To be determined
VI. Project Management and Organization
· Project Organization
_No committee impacts at current
· Other
_Committee impacts are foreseeable if the project is accepted
VII. Estimated Financial Plan
_Aside from estimated costs of $ 600,000 – no financial plans have been developed
VIII. Estimated Work Plan
_Estimated timeframe is 1 to 2 years from time of project initiation
_No resources have been allocated for this project at current
_Patent application foreseeable
IX. Discussion
_Further review of the justification, the proposal, planning, etc. is needed and desirable if the project is accepted
X. Feasibility
_
Feasibility study may be needed upon approval of the project and study/studies
Links to Proposed Suppliers
AR Worldwide (
http://www.ar-worldwide.com/html/00000.asp)
BetaBatt (
http://www.betabatt.com/)
DSM (
http://www.dsm.com/en_US/html/hpf/home_dyneema.htm)
Modern Plastics(
http://modernplastics.com/victrex_peek_plastic.html?src=google&gclid=CK7fhcfep40CFQyIPgodyh480g)
Para Tech (
http://www.seaanchor.com/seaanchor.htm)
Qynergy (
http://www.qynergy.com/)
Signal Forge (
http://www.signalforge.com/)
Links to Data for Proposed Equipment
1S1G4A PDF document (
http://www.arww-rfmicro.com/post/1S1G4A.pdf)
Anchor (
http://www.biggideas.com/sea-anchor/html/prices.html)
Dyneema Yarn (
tensile and creep properties) and PDF document (
http://www-lgm2b.iut.u-bordeaux1.fr/publi/PE%20fibre.pdf)
Radioisotope Battery (
http://en.wikipedia.org/wiki/Radioisotope_battery)%20%20and%20(http://www.physorg.com/news4081.html)
New “Nuclear Battery” Runs 10 Years, 10 Times More Powerful and
Americium Battery(
http://www.tfot.info/articles.php?itemId=26/64/)
SF 1000(E) (
http://www.signalforge.com/home/sf1/index_main.html) and PDF document (
http://www.signalforge.com/shop/images/SF1000_DS30.pdf)
Victrex (
PEEK) (
http://en.wikipedia.org/wiki/PEEK) and
(
http://modernplastics.com/victrex_peek_plastic.html?src=google&gclid=CK7fhcfep40CFQyIPgodyh480g)
Links to Other References in Proposal
2017, 2026, 2039(
http://newton.dm.unipi.it/cgi-bin/neodys/neoibo?objects:Apophis;ephpred)
40 foot anchor
Prices(
http://www.biggideas.com/sea-anchor/html/prices.html)
Aerospace and Defense Benchmarking (
http://www.adbcbenchmarking.com/)
99942 Apophis (
http://en.wikipedia.org/wiki/99942_Apophis)
AR RF Microwave Instrumentation(
http://www.ar-worldwide.com/rf_microwave_instrumentation.htm)
Aten Asteroid (
http://en.wikipedia.org/wiki/Aten_asteroid)
Award Abstract #0320029 (
Award#0320029 - SBIR Phase I: A Semiconductor Device for Direct and Efficient Conversion of Radioisotope Energy)
Battery Power Source (
http://en.wikipedia.org/wiki/Radioisotope_battery)
BetaBatt (
http://betabatt.com/)
Brewster, Washington (
48°07′52.42″N, 119°40′59.80″W)
[
http://tools.wikimedia.de/~magnus/geo/geohack.php?params=48_07_52.42_N_119_40_59.80_W_%7B%7B%7B9%7D%7D%7D]
A dangerous planetary body (
http://neo.jpl.nasa.gov/neo/report2007.html)
Dealing with the Impact Hazard(
http://nai.arc.nasa.gov/impact/downloads/NEO_Chapter_1.pdf)
Discovery is NEAR (
http://near.jhuapl.edu/)
DSM - DSM Dyneema - Dyneema® Yarn(
http://www.dsm.com/en_US/html/hpf/dyneema_yarn.htm)
Error Ellipse(
http://www.sli.unimelb.edu.au/nicole/surveynetworks/02a/notes09_01.html)
Feasibility study (
http://en.wikipedia.org/wiki/Feasibility_study)
First Space Tug Set to Launch in 2007(
http://www.newscientist.com/article.ns?id=dn4992)
Fort Davis, Texas (
30°38′06.11″N, 103°56′41.34″W)
[
http://tools.wikimedia.de/~magnus/geo/geohack.php?params=30_38_06.11_N_103_56_41.34_W_%7B%7B%7B9%7D%7D%7D]
Geometric delay(
http://scienceworld.wolfram.com/physics/SynthesisImagingGeometricDelay.html)
Hancock, New Hampshire (
42°56′00.99″N, 71°59′11.69″W)
[
http://tools.wikimedia.de/~magnus/geo/geohack.php?params=42_56_00.99_N_71_59_11.69_W_%7B%7B%7B9%7D%7D%7D]
Harvard Smithsonian Center for Astrophysics (
http://cfa-www.harvard.edu/)
Homeland Currency Security (
http://homelandcurrencysecurity.blogspot.com/)
Image:2004mn4d5 s.gif (
Image:2004mn4d5 s.gif - Wikipedia, the free encyclopedia)
Information Services Board website(
http://isb.wa.gov/committees/coresystems/justification.aspx)
ISBN: 0-471-25492-4 (
http://books.google.com/books?id=sdMEAAAACAAJ&dq=Interferometry+and+Synthesis+in+Radio+Astronomy)
JPL Small-Body Database Browser (
http://ssd.jpl.nasa.gov/sbdb.cgi?sstr=99942&orb=1)
J. Wiley & Sons (
http://www.wiley.com/WileyCDA/)
Jet Propulsion Laboratory (
http://www.jpl.nasa.gov/)
Kitt Peak,
Arizona (
31°57′22.70″N, 111°36′44.72″W)
[
http://tools.wikimedia.de/~magnus/geo/geohack.php?params=31_57_22.70_N_111_36_44.72_W_%7B%7B%7B9%7D%7D%7D]
KT event (
Cretaceous–Tertiary extinction event - Wikipedia, the free encyclopedia)
Los Alamos, New Mexico (
35°46′30.45″N, 106°14′44.15″W)
[
http://tools.wikimedia.de/~magnus/geo/geohack.php?params=35_46_30.45_N_106_14_44.15_W_%7B%7B%7B9%7D%7D%7D]
Low Cost RFID Labels/”Tapes”/”Tags”/”Devices”(
http://homelandcurrencysecurity.blogspot.com/2006/08/low-cost-rfid-labelstapestagsdevices.html)
MAST [Program] (
http://www.spaceref.com/news/viewpr.rss.html?pid=22390)
Mauna Kea,
Hawaii (
19°48′04.97″N, 155°27′19.81″W)
[
http://tools.wikimedia.de/~magnus/geo/geohack.php?params=19_48_04.97_N_155_27_19.81_W_%7B%7B%7B9%7D%7D%7D]
MPa (
http://en.wikipedia.org/wiki/Pascal_(unit))
NASA (
http://www.nasa.gov/home/)
National Radio Astronomy Observatory (
http://www.nrao.edu/)
National Science Foundation (Radioisotope battery grant)NEAR-Shoemaker became the first spacecraft to land on an asteroid(
http://apod.nasa.gov/apod/ap010213.html)
Near Earth Object (
http://neo.jpl.nasa.gov/)
Near Earth Object Program (
http://neo.jpl.nasa.gov/neo/report2007.html)
NeoDys Ephemerides(
http://newton.dm.unipi.it/cgi-bin/neodys/neoibo?objects:Apophis;ephpred)
North Liberty, Iowa (
41°46′17.13″N, 91°34′26.88″W)
[
http://tools.wikimedia.de/~magnus/geo/geohack.php?params=41_46_17.13_N_91_34_26.88_W_%7B%7B%7B9%7D%7D%7D]
NOI (Notice of Intent)[
http://www.rfp-templates.com/search/for/Notice-of-Intent-Template.html]
Orbital Recovery Gives Go-ahead for its ConeXpress Space Tug; Production to Start in September, First Launch Planned in 2007 (
http://www.orbitalrecovery.com/news9.html)
Operational effectiveness(
http://www.realisation.com.au/site1/Articles/Operational%20effectiveness.htm)
Owens Valley,
California (
37°13′53.95″N, 118°16′37.37″W)
[
http://tools.wikimedia.de/~magnus/geo/geohack.php?params=37_13_53.95_N_118_16_37.37_W_%7B%7B%7B9%7D%7D%7D]
PEEK (
Polyetheretherketone plastic) [
http://en.wikipedia.org/wiki/PEEK]
Pie Town,
New Mexico (
34°18′03.61″N, 108°07′09.06″W)
[
http://tools.wikimedia.de/~magnus/geo/geohack.php?params=34_18_03.61_N_108_07_09.06_W_%7B%7B%7B9%7D%7D%7D]
Precision estimates of universal time from radio-interferometric observations(http://adsabs.harvard.edu/abs/1979IAUS...82..225W)
Public Law No. 109-155(
http://www7.nationalacademies.org/ocga/Laws/PL109_155.asp)
Qynergy (
http://www.qynergy.com/)
Radio Frequency Amplifier(
http://www.arww-rfmicro.com/html/12100_rf_amplifier.asp)
Radio Frequency Signal Generator(
http://www.signalforge.com/shop/images/SF1000_DS30.pdf)
Radio Interferometer(
http://www.drao-ofr.hia-iha.nrc-cnrc.gc.ca/science/vlbi/principles/principles.shtml)
RFID (
http://en.wikipedia.org/wiki/Rfid)
RFP (Request for Proposals) [
http://en.wikipedia.org/wiki/RFP]
Signal Forge SF1000(
http://www.signalforge.com/shop/images/SF1000_DS30.pdf)
Sec. 101 (RESPONSIBILITES, POLICIES & PLANS) (2) (B) (i) & (2) (B) (
http://www7.nationalacademies.org/ocga/Laws/PL109_155.asp)
“Simple Radio Interferometry” (
http://fringes.org/)
Spaceguard (
http://spaceguard.esa.int/)
St. Croix,
United States Virgin Islands (
17°45′23.68″N, 64°35′01.07″W)
[
http://tools.wikimedia.de/~magnus/geo/geohack.php?params=17_45_23.68_N_64_35_01.07_W__]
“tag” (
http://planetary.org/programs/projects/apophis_competition/20070523.html)
tensile and creep properties (UHMWPE) [
http://www-lgm2b.iut.u-bordeaux1.fr/publi/PE%20fibre.pdf]
Tensile strength (
http://en.wikipedia.org/wiki/Tensile_strength)
Tether Anchor (
http://www.biggideas.com/sea-anchor/html/prices.html)
Tethers Unlimited website (
http://www.tethers.com/TethersGeneral.html)
Transmitter Protection(
http://modernplastics.com/victrex_peek_plastic.html?src=google&gclid=CK7fhcfep40CFQyIPgodyh480g)
Tunguska Event (
http://en.wikipedia.org/wiki/Tunguska_event)
ultra high vacuum (
http://en.wikipedia.org/wiki/Ultra-high_vacuum)
UMWPE (Ultra High Molecular Weight Polyethylene) Yarn(
http://www.dsm.com/en_US/html/hpf/dyneema_yarn.htm)
United States Patent Office (
http://www.uspto.gov/)
University of Illinois at Urbana-Champaign (
http://cfa-www.harvard.edu/)
Very Large Array (VLA) (
http://www.vla.nrao.edu/)
Very Long Baseline Array (
http://www.vlba.nrao.edu/)
Very Large Array sites (
http://www.nrao.edu/telescopes/)
Victrex Peek Plastic Source(http://modernplastics.com/victrex_peek_plastic.html?src=google&gclid=CK7fhcfep40CFQyIPgodyh480g)
Young Engineer’s Satellite 2 Project (
http://www.yes2.info/)
Young’s Modulus (
http://en.wikipedia.org/wiki/Young)
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