Aeronautics and astronautics – Aircraft sustentation – Sustaining airfoils
Reexamination Certificate
1999-10-22
2001-07-17
Eldred, J. Woodrow (Department: 3644)
Aeronautics and astronautics
Aircraft sustentation
Sustaining airfoils
C244S003270, C244S03500A, C244S124000, C244S158700
Reexamination Certificate
active
06260798
ABSTRACT:
CROSS-REFERENCE TO RELATED APPLICATIONS
Not Applicable
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH
Not Applicable
REFERENCE TO MICROFICHE APPENDIX
Not Applicable
BACKGROUND OF THE INVENTION
The present invention relates to flying structures that derive lift from associated aerodynamic surfaces, and more particularly, to such flying structures constructed and arranged so as to be deployed from a compact, stowed payload state, and withstand ballistic g-forces while in such a stowed payload state.
Reconnaissance and surveillance are universally recognized as key components of typical investigatory operations; this is especially true for military operations. Such observation tools may be used to identify and evaluate potential targets, provide targeting information to weapons platforms, and battle damage assessment following a sortie. The three general classes of observation tools currently used for reconnaissance/surveillance missions in military operation, as shown in
FIG. 1
, include 1) satellites, 2) high altitude/long endurance systems (e.g., JSTARS, Tier II+, U-2, etc.), and 3) tactical UAVs (e.g., Outrider, Pioneer, Hunter II, etc.). Satellites provide global coverage and high resolution information, but are typically the most expensive options and exhibit the longest response time. High altitude/long endurance systems are typically less expensive and exhibit faster response times than satellites, but provide reduce coverage (i.e., theater level rather than global). Tactical UAVs are the least expensive class of observation tools and provide the fastest response times, but provide only battlefield coverage. The cost of the observation tool is directly related to the level of command to which the tool is available. In many scenarios, it is advantageous to make an observation tool available to the lowest level of command possible. Making such tools available to lower levels of command increases battle efficiency by reducing the amount of time necessary make targeting decisions. Thus, a disadvantage to such prior art observation tools is that they are not directly available to the levels of command that could most efficiently utilize them.
Another disadvantage to such prior art observation tools is the risk involved in transporting the observation tools to a location that will provide the most valuable observation information. Because such tools often travel at sub-sonic speeds, there is a significant probability that the tool will be detected, intercepted and/or destroyed by hostile forces. One possible solution to such risk is to ballistically launch the observation tool to the desired location. However, prior art observation tools are not typically constructed to survive the high g-forces that develop during a ballistic launch. Observation tools that include aerodynamic surfaces for sustained flight are particularly vulnerable, due to the inherently fragile nature of such surfaces.
It is an object of the present invention to substantially overcome the above-identified disadvantages and drawbacks of the prior art.
SUMMARY OF THE INVENTION
The foregoing and other objects are achieved by the invention which in one aspect comprises a multi-state, aerodynamic wing assembly constructed and arranged to have a first state which is compact and adapted to withstand a substantial force due to acceleration in at least one direction, and a second state adapted for flying. The wing includes at least two airfoil sections, each of the airfoil sections having a span-wise axis, and a airfoil cross section normal to the span axis. The airfoil sections are preferably disposed mutually adjacent and end to end. The wing further includes a pivot assembly fixedly attached to each pair of adjacent ones of the airfoil sections at an end of each of the adjacent airfoil sections along said span-wise axis. The pivot assembly forms an articulation axis for angular translation of each the pair of airfoil sections, such that the wing assembly converts, upon a predetermined stimulus, from a stowed configuration characterized by nested airfoil sections, to a deployed configuration characterized by a substantially uninterrupted aerodynamic surface.
In another embodiment of the invention, the pivot assembly includes at least one hinge assembly.
In another embodiment of the invention, the pivot assembly includes at least one flex joint assembly.
In another embodiment of the invention, the pivot assembly further includes at least one actuator for forcing each pair of the airfoil sections to translate with respect to one another about the articulation axis, such that the wing assembly converts from the stowed configuration to the deployed configuration.
In another embodiment of the invention, the actuator includes a spring assembly; in particular, the spring assembly may further include a torsion spring assembly.
In another embodiment of the invention, the relative movement between each the pair of airfoil sections includes approximately 180 degrees of relative movement about the articulation axis, from the stowed configuration to the deployed configuration.
In another embodiment of the invention, at least one aerodynamic force converts the wing assembly from a stowed configuration to a deployed configuration.
In another embodiment, a combination of at least one aerodynamic force and at least one torsion spring converts the wing assembly from a stowed configuration to a deployed configuration.
In another embodiment of the invention, the wing assembly further includes at least one locking mechanism for locking the wing segments in the deployed configuration.
In another embodiment of the invention, the at least two airfoil sections includes N airfoil sections, joined by N−1 pivot assemblies and forming N−1 articulation axes, where N is an integer greater than or equal to two.
In another embodiment of the invention, the N airfoil sections includes six airfoil sections, joined by five pivot assemblies and forming five airfoil sections.
In another embodiment of the invention, the N−1 articulation axes are substantially parallel.
In another embodiment of the invention, the N−1 articulation axes are non-parallel, such that the deployed configuration includes a spiral wing.
In another embodiment of the invention, the pivot assembly further includes nesting supports, constructed and arranged such that predetermined pairs of the nesting supports are adjacent while in the stowed configuration, so as to provide structural support along the span-wise axis.
In another embodiment of the invention, the at least one direction of acceleration includes the span-wise axis.
In another embodiment of the invention, each the airfoil cross section includes a modified T16 airfoil section.
In another embodiment of the invention, each of the airfoil sections includes 7075 aluminum.
In another embodiment of the invention, each of the airfoil sections and corresponding pivot assemblies are machined from a unitary body of 7075 aluminum.
In another embodiment of the invention, each of the airfoil sections includes a composite material.
In another embodiment of the invention, each of the airfoil sections is constructed via a fabrication technique selected from the group consisting of molding, injection molding, casting, stamping and extrusion.
In another embodiment of the invention, the wing assembly is constructed and arranged so as to withstand at least one acceleration force in at least one direction.
In another embodiment of the invention, the wing assembly is constructed and arranged so as to withstand a 15,000 g forward acceleration force, and a 4,000 g rebound acceleration force.
In another aspect, the invention comprises a flying structure constructed and arranged so as to withstand an acceleration force directed along a main axis. The flying structure includes a body disposed about the main axis, and at least one wing assembly pivotally mounted to the body. The wing assembly is constructed and arranged so as to convert, upon a predetermined stimulus, from a stowed configuration characterized by neste
Casiez Thierry
Cesnik Carlos
Drela Mark
Jenkins Staci N.
Spearing Mark
Eldred J. Woodrow
Massachusetts Institute of Technology
McDermott & Will & Emery
LandOfFree
High-G compact folding wing does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with High-G compact folding wing, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and High-G compact folding wing will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-2522401