Buoyantly propelled submerged canister for air vehicle launch

• US 6,286,410 B1
• Filed: 05/10/1999
• Issued: 09/11/2001
• Est. Priority Date: 05/10/1999
• Status: Expired due to Fees

• Current Assignee: Secretary of The Navy United States Government As Represented By The
• Original Assignee: The United States of America As Represented By The Secretary of Agriculture
• Inventors: Leibolt, Edward A.
• Primary Examiner(s): ELDRED, JOHN W
• Application Number:
  US09/307,420
• Time in Patent Office: 855 Days
• Field of Search: 89/18.09, 89/18.1
• US Class Current: 89/1.809
• CPC Class Codes: F41F 3/07 Underwater launching-apparatus

Abstract

The invention features a self-contained enclosure-plus-enclosed contexture and the implementation thereof in a multi-phase launching system, according to which the waterborne first phase entails naturally (buoyantly) induced motion, and at least the airborne second phase entails artificially (technologically) induced motion. Typical inventive practice provides a launch canister which is exteriorly configured to be hydrodynamically efficient while moving buoyantly upward in response to hydrostatic pressure, and which has a chamber for stowing an air vehicle. The inventive vehicle-stowing canister is released underwater so as to be buoyantly propelled upward and into the air, at which time the air vehicle is mechanistically propelled (e.g., boosted), in response to which the canister becomes disjointed cooperatively with the uncoupling of the air vehicle from the canister. The air vehicle continues to propulsively ascend, the canister'"'"'s nose cone and main body gravitationally falling to the water below. Some inventive embodiments enter an airborne third phase (which, like the second phase, entails artificially induced motion), wherein the air vehicle'"'"'s aerodynamic shape is adjusted (e.g., the wings are extended) and its main (self) propulsion (e.g., via propeller or jet engine) is initiated.

Claims

1. Apparatus comprising a canister, an air vehicle, discharge means and sensing means;

said air vehicle having a fore vehicle end and an aft vehicle end, said sensing means being operatively connected to said canister, said sensing means being capable of sensing a physical change associated with the desubmergence of at least a portion of said canister, said sensing means being capable of sending a communication in accordance with said physical change, said discharge means being situated at said aft vehicle end and being capable of activation, as a result of said communication sent by said sensing means, so as to propel said air vehicle in a forward direction;

said canister including an approximately cylindrical body and a nose cone, said body including an interior space for containing said air vehicle, said interior space being characterized by an upper interior space end and a lower interior space end, said upper interior space end being open, said lower interior space end being closed, said interior space having an transverse interior space surface portion at said lower interior space end, said nose cone including a generally conical section and an approximately cylindrical shoulder section, said conical section having a generally narrower conical end and a generally wider conical end, said shoulder section protecting from said conical section at said wider conical end, said shoulder section including an approximately circular bottom shoulder surface portion, said shoulder section having an approximate shoulder diameter, said conical section having an approximate wider conical diameter at said wider conical end, said body having an approximate body diameter, said shoulder diameter being less than said wider conical diameter and being less than said body diameter;

said body and said nose cone being capable of being securely coupled with each other so that said shoulder section fits inside a portion of said interior space at said upper interior space end, so that said conical section and said cylindrical body are approximately flush, so that said conical section, said shoulder section and said body are each approximately symmetrical with respect to the same imaginary longitudinal axis, so that said transverse interior space surface portion and said bottom shoulder surface portion each approximately define a plane which is approximately perpendicular with respect to said imaginary longitudinal axis, and so that said interior space accommodates said air vehicle;

when said body and said nose cone are securely coupled with each other, said air vehicle being adaptable to containment in said interior space, and said body and said nose cone being capable of being uncoupled from each other, so that said fore vehicle end is in the vicinity of said upper interior space end, so that said aft vehicle end is in the vicinity of said lower interior space end, and so that, as a result of said activation of said discharge means, said body and said nose cone are capable of being uncoupled from each other whereby said air vehicle separates from said body and said nose cone, wherein upon said activation of said discharge means said discharge means exerts an aftward force and said fore vehicle end exerts a forward force, said aftward force being exerted by said discharge means against said transverse interior space surface portion, said forward force being exerted by said fore vehicle end against said bottom shoulder surface portion, said aftward force and said forward force thereby causing said uncoupling of said body and said nose cone whereby said air vehicle separates from said body and said nose cone;

when said body and said nose cone are securely coupled with each other, said canister being capable of liquid buoyantly propelled upward movement and being adaptable to being released from a submerged location, said canister, in association with said liquid buoyantly propelled upward movement of said canister, being characterized by a shape which at least substantially minimizes drag and at least substantially maximizes stability.

2. Apparatus as in claim 1, wherein said sensing means includes means for sensing the pressure change associated with the desubmergence of at least a portion of said structure.

3. Apparatus as in claim 2, wherein

said apparatus comprises means for initiating said activation of said discharge means, wherein said means for initiating receives said communication from said sensing means.

4. Apparatus as in claim 3, wherein said apparatus comprises means for releasing said canister from said submerged location.

5. Apparatus as in claim 1, wherein:

said buoyantly propelled upward movement approximately defines a vertical direction;

said canister includes stabilization means; and

said imaginary longitudinal axis and said vertical direction are approximately coincident.

6. Apparatus as in claim 1, wherein:

said buoyantly upward movement is approximately vertical;

said canister includes stabilization means; and

the orientation of said canister is approximately vertical, said conical section up, during said liquid buoyantly upward movement.

7. Apparatus as in claim 6, wherein said stabilization means includes a plurality of fins.

8. Apparatus as in claim 7, wherein

said body has an upper body end and a lower body end;

said nose cone is situated at said upper body end; and

said fins are situated in the vicinity of said lower body end.

9. Apparatus as in claim 2, wherein said means for sensing the pressure change is situated in said nose cone.

10. Apparatus as in claim 9, wherein said pressure change is associated with the desubmergence of at least a portion of said conical section of said nose cone.

11. Apparatus as in claim 10, wherein

said apparatus comprises control means, wherein said control means includes means for initiating said activation of said discharge means, and wherein said means for initiating receives said communication from said sensing means.

12. Apparatus as in claim 11, wherein said air vehicle is a winged air vehicle, said winged air vehicle including a fuselage and at least two aero structures, said at least two aero structures being selected from the group consisting of wing, flap, aileron and rudder, said at least two aero structures being capable of compliancy in order that said interior space of said canister accommodate said winged air vehicle when said body and said nose cone are securely coupled with each other, said compliancy being selected from the group consisting of movability, adjustability, retractability, rotatability, pivotability, flexibility and foldability, said at least two aero structures being capable of decompliancy after said winged air vehicle separates from said body and said nose cone.

13. Apparatus as in claim 8, wherein:

said sensing means includes means for sensing the pressure change associated with the desubmergence of at least a portion of said structure, said means for sensing the pressure change being situated in said nose cone;

said communication sent from said sensing means is a first communication;

said apparatus comprises control means situated in said body, said control means being capable of receiving said first communication from said sensing means;

said control means is capable of sending a second communication in accordance with said first communication; and

said discharge means is capable of receiving said second communication from said control means.

14. Apparatus as in claim 13, wherein:

said control means includes a controller, a switch and a power supply;

said discharge means includes a propulsor and an actuator for said propulsor;

said means for sensing the pressure change is capable of sensing pressure change associated with environmental change from water to air;

said sensing means is capable of informing said controller of said pressure change, said first communication including said informing said controller of said pressure change; and

said controller is capable, upon being informed of said pressure change, of opening said switch, whereupon electrical current flows from said power supply to said actuator, said second communication including said electrical current flowing from said power supply to said actuator.

15. Apparatus as in claim 14, wherein:

said power supply includes a battery;

said propulsor includes a rocket motor; and

said actuator includes an ignitor for said rocket motor.

16. Apparatus as in claim 14, wherein:

said power supply includes a battery;

said propulsor includes a spring; and

said actuator includes a solenoid.

17. A system for launching a vehicle from an aquatic environment to an aerial environment, said vehicle having a front vehicle area and a back vehicle area, said system comprising:

a canister for containing said vehicle, said canister being configured in furtherance of reducing drag and increasing stability in relation to the upward motivation of said canister by a buoyant force in said aquatic environment;

a device for releasing said canister from a location in said aquatic environment, thereby permitting said upward motivation of said canister; and

a propulsor for propelling said vehicle from said canister after the transition of said canister from said aquatic environment to said aerial environment, said propulsor being attachable to said vehicle at said back vehicle area;

said canister including a cylindroid member and a nose cone member, said cylindroid member having a cavity and an opening into said cavity, said cavity having an extreme wall opposite said opening, said cylindroid member having a first cylindroid end and a second cylindroid end, said opening being located at said first cylindroid end, said extreme wall being located between said first cylindroid end and said second cylindroid end, said nose cone member including a generally cone-shaped portion and an approximately cylindrical projection axially aligned with said cone-shaped portion, said projection including an approximately round end face, said cylindroid member and said nose cone member being joinable and disjoinable;

said cylindroid member and said nose cone member being joinable whereby;

said projection is approximately fully inserted into said cavity at said opening;

a portion of said cavity is unoccupied by said projection; and

said vehicle is containable in said unoccupied portion of said cavity, said front vehicle area being located proximate said end face of said projection, said back vehicle area being located proximate said extreme wall of said cavity;

said cylindroid member and said nose cone member being disjoinable whereby;

said propulsor by said propelling effects pushing against said extreme wall of said cavity;

said front vehicle area contactingly pushes against said end face of said projection; and

said vehicle separates from said cylindroid member and said nose cone member.

18. A system for launching as in claim 17, comprising:

an actuator for said propulsor;

a battery;

a switch for closing the electric circuit between said battery and said actuator;

a pressure transducer for transmitting a signal to said controller in relation to said transition; and

a controller for activating said switch upon receipt of said signal.

19. A system for launching as in claim 18, wherein said propulsor includes a rocket motor, and wherein said actuator includes a rocket ignitor.

20. A system for launching as in claim 18, wherein said propulsor includes a spring device, and wherein said actuator includes a solenoid.

21. A system for launching as in claim 20, wherein said device is a nonexplosive mechanical device, wherein said canister includes plural stabilizing foils, wherein said propulsor is a booster propulsor, and wherein said system comprises a main propulsor for said vehicle, said main propulsor commencing operation upon termination of operation of said booster propulsor.

22. A method for launching an object from a site below the surface of a body of water, said object having a front object region and a back object region, said method comprising:

providing an enclosure, said enclosure being contoured for promoting hydrodynamic efficiency when impelled by buoyancy, said enclosure including a cylindroid structure and a nose cone structure, said cylindroid structure having a chamber and an opening into said chamber, said chamber having an extreme wall opposite said opening, said cylindroid structure having a first cylindroid end and a second cylindroid end, said opening being located at said first cylindroid end, said extreme wall being located between said first cylindroid end and said second cylindroid end, said nose cone structure including a generally cone-shaped portion and an approximately cylindrical projection axially aligned with said cone-shaped portion, said projection including an approximately round end face, said cylindroid structure and said nose cone structure being joinable and disjoinable;

associating propulsion apparatus with said object at said back object region, said propulsion apparatus being for propelling said object;

associating sensing apparatus with said enclosure at said nose cone structure, said sensing apparatus being for sensing fluid pressure relating to the fluid external to said enclosure;

placing said object in said chamber;

joining said cylindroid member and said nose cone member, so that;

said projection is approximately fully inserted into said chamber at said opening;

a portion of said chamber is unoccupied by said projection; and

said object is positioned in said unoccupied portion of said chamber, said front object region being located proximate said end face of said projection, said back object region being located proximate said extreme wall of said chamber;

releasing said enclosure from said site, said object enclosed, so that said enclosure is buoyantly impelled to rise toward, through and above said surface;

sensing fluid pressure relating to the fluid external to said enclosure; and

propelling said object from said enclosure once said enclosure has risen above said surface, so that;

said propulsion apparatus, through said propelling, exerts a force against said extreme wall of said chamber;

said front object region comes into contact with, and exerts a force against, said end face of said projection;

said cylindroid member and said nose cone member are disjoined, due to said exertion of force by said propulsion apparatus, and due to said exertion of force by said front object region; and

said object separates from said cylindroid member and said nose cone member.

23. A method for launching as in claim 22, wherein said object is a winged aircraft having a plurality of wings, said method comprising providing said winged aircraft so as to be characterized by adjustability of said wings for permitting said enclosing of said winged aircraft in said enclosure.

24. A method for launching as in claim 23, comprising:

providing said sensing apparatus for said sensing;

providing said propulsion apparatus for said propelling; and

providing control apparatus for;

communicating with said sensor and with said propulsion apparatus;

receiving, from said sensor, information pertaining to said sensing; and

controlling said propulsion apparatus based on said information, whereby said propelling is performed when said fluid external to said enclosure is air.

25. A method for launching as in claim 24, wherein:

said method comprises, prior to said releasing, evaluating the speed of said enclosure at about the time that said enclosure reaches said surface, said evaluating including regarding at least one factor selected from the group of factors consisting of;

distance of said site below said surface;

size of said enclosure;

shape of said enclosure; and

mass distribution of said enclosure; and

said releasing includes selecting said site in consideration of said evaluating.

26. A method for launching as in claim 22, wherein said method comprises providing said object, wherein said object is selected from the group of objects consisting of missile, rocket, projectile, unmanned helicopter, manned helicopter, unmanned winged aircraft and manned winged aircraft.

27. A method for launching as in claim 23, wherein said winged aircraft is capable of self-propulsion suitable for sustained flight, and wherein said method comprises, after propelling said winged aircraft from said enclosure, causing said self-propulsion to commence.