Modularized airplane structures and methods

• US 20080217470A1
• Filed: 03/06/2008
• Published: 09/11/2008
• Est. Priority Date: 03/07/2007
• Status: Active Grant

• Current Assignee: Zhao Jie
• Original Assignee: Zhao Jie
• Inventors: Zhao, Jie
• Granted Patent: US 8,256,714 B2
• Time in Patent Office: Days
• US Class Current: 244/99.3
• CPC Class Codes: A63H 27/02 Model aircraft
• CPC Class Codes: A63H 29/22 Electric drives power supply through track A63H18/12

Abstract

A modularized airplane includes two separably interconnected modules. The first module, incorporating substantial airplane style characteristics, comprises wings and stabilizers having at least one associated control surface joined with a fuselage portion. The second module carries a set of essential airplane components interconnected to suffice airplane operations including a propulsion unit, radio receiver and/or auto-piloting electronics unit, control servo devices, and power means mounted on provided support structures. At least one pair of mutually magnetically attractive connectors oppositely affixed on said two module members provide means for inter-modular structural connection. An alignment mechanism having oppositely provided complementary structures on said two modules facilitate alignment as well as lateral interlocking for inter-modular structural connection. A linkage means includes two linkage portions separably connected by two mutually magnetically attractive elements oppositely mounted thereon to form a linkage assembly for linking between control surfaces and associated servo devices, a linkage guide means, and a stress isolation mechanism. The structural connection and the control linkage means facilitate substantially effortless inter-modular connections to form a functional modularized airplane as well as excessive parting tension induced nondestructive inter-modular disconnection. Multiple modules of differing styles and aerodynamic specifications can be made as the first module to be interconnected with the second module to form differing airplanes, sharing essential components, for various applications.

Claims

1. A modularized airplane, comprising:

(a) a first module member having first fuselage portion, at least one aerodynamically functional fin fixedly joined with said first fuselage portion, and at least one flight control surface having a control coupling lever fixedly secured thereon, movably attached to at least one said fin;

(b) a second module member having second fuselage portion complementary to the first fuselage portion of said first module member (a) in forming an airplane fuselage, support structures provided on said second fuselage portion, a plurality of operatively interconnected essential flight-providing and control-providing components mounted on said support structures including a propulsion device for providing thrust, at least one servo means associated with said flight control surface of first module member (a) for controlling the angular position of the control surfaces, control electronics circuitry means for controlling said propulsion device and said servo means, and power means for powering onboard power consuming components including said propulsion device and said servo means;

(c) a connection means for detachably interconnecting said complementary fuselage portions of said first module member (a) and said second module member (b) to ensure the structural and aerodynamic integrity of the integral modularized airplane;

(d) a linkage means for operatively interconnecting said flight control surface of first module member (a) and said servo means of second module member (b) for transmitting control motion from said servo means to said flight control surface to control the angular position of said control surface, and allowing excessive-linkage-stress-induced nondestructive linkage disconnection;

whereby, the modularized airplane may be formed by interconnecting said first module member (a) and said second module member (b) by said connection means (c) to form an airplane of complete structure, and interconnecting said control surface and said servo means by said linkage means (d);

whereby, the modularized airplane may be intentionally disassembled into separate modules by structurally detaching said first and said second module members (a) and (b) from one another by said connection means (c), and, as allowed by said linkage means (d) applying excessive control-linkage-wise parting tension to nondestructively delink said servo means from said flight control surface;

whereby, in case of an unintentional structural separation of said first and said second module members (a) and (b) resulting in excessive control linkage tension said flight control surface and said servo means will nondestructively disconnect as allowed by said linkage means (d);

whereby, both and either said module members can incorporate differing styles and aerodynamic characteristics to form differing airplanes.

2. The modularized airplane of claim 1, wherein said connection means (c) further allowing structurally nondestructive disconnection of the modularized airplane into structurally separated individual module members under inter-modular structural stress exceeding a predetermined limit;

whereby, said connection means (c) and said linkage means (d) together enable substantially effortless intentional nondestructive disassembly of the integral airplane into separate module members by applying excessive inter-modular parting stress to structurally disconnect said module members and subsequently applying excessive control linkage parting tension to de-link control linkages;

whereby, said connection means (c) and said linkage means (d) together enable nondestructive disassembly of the integral airplane into separate module members under unintentional excessive structural and linkage tension situations, such as in an event of airplane crash, to minimize excessive stress- and tension-related airplane damages.

3. The modularized airplane of claim 2, wherein the connection means (c) further including at least one pair of mutually magnetically attractive and operatively matching members connectable to one another by said mutual magnetic attraction force, and affixed oppositely at predetermined locations on said first module member (a) and said second module member (b), for the purpose of structurally interconnecting said first module to said second module, the magnitude of said magnetic attraction force is selected for the inter-modular structural connection to withstand the modularized airplane structure-wise stress under allowed operation conditions, as well as to enable structurally nondestructive disconnection of the modularized airplane into structurally separated individual module members under excessive structural stress;

whereby, when said first module member and said second module member are brought to a spatial proximity where at least one pair of said magnetically attractive members experience sufficient mutual magnetic attraction to result in progressive pair-wise connection, substantial automatic modular structural interconnection occurs.

4. The modularized airplane of claim 3, wherein said connection means (c) further including two mutually physically matching and laterally interlocking structure sections provided oppositely at predetermined locations on said first module member (a) and said second module member (b), adapted to be in mutually matching and interlocking position when said first module member (a) and said second module member (b) are structurally interconnected;

whereby, one said structure section forms a physical acceptance for said matching structure section allowing progressively smaller lateral misalignment between said two opposing magnetically attractive members in each of said pairs as the mutually magnetically attractive members in said pairs approaching progressively closer to one another. Said two structure sections match and laterally interlock with one another ensuring precise inter-modular structural alignment when said opposing magnetically attractive members in said pairs connect to one another, thus providing guidance and alignment for inter-modular structural interconnection, as well as lateral relative movement limit for interconnected module members.

5. The modularized airplane of claim 2, wherein said linkage means (d) further including a first linkage portion and a second linkage portion, coupling means provided for said first linkage portion to operatively couple to said servo means, coupling means provided for said second linkage portion to operatively couple to said control surface associated with said servo means, a pair of mutually magnetically attractive and operatively matching members affixed at predetermined locations on said first linkage portion and said second linkage portion, respectively, for connecting said two linkage portions to form one linkage assembly member operatively linking said control surface and said associated servo means, the magnitude of said mutual magnetic attraction force is selected for said one linkage assembly member to withstand the modularized airplane control-linkage-wise tension under allowed operation conditions, as well as to enable nondestructive disconnection of said one linkage assembly into said linkage portions under excessive control-linkage-wise tensions.

6. The modularized airplane of claim 5, wherein said linkage means (c) further including a linkage guide means for limiting the spatial orientation for said linkage portions so that, when said first module member (a) and said second module member (b) are connected by connection means (c), said two mutually magnetically attractive members will be positioned sufficiently near one another to result in substantial automatic connection of said two linkage portions by magnetic attraction force, thus forming said one control linkage assembly.

7. The modularized airplane of claim 6, wherein said linkage guide means of said control linkage means (c) including a rigid guide member for said generally elongated linkage portions, said guide member has a through hole forming an aperture through which said elongated linkage portion extends, said guide member is mounted on the same module member having the device said linkage portion is linked to, and the size and shape of said aperture are adapted not to obstruct linkage transmission of control motion.

8. The modularized airplane of claim 6, wherein said one linkage assembly further including:

a first structure, rigid, provided or extending from a predetermined location on said one linkage member;

a second structure, rigid, provided on or extended from said first module member in physical relationship with said first structure forming a longitudinal movement limit for said one linkage assembly member and therefore forming a limited operating range for said control surface;

whereby, upon reaching said longitudinal movement limit said first structure is in physical contact with said second structure, thus preventing said one linkage assembly from further longitudinal movement, and further longitudinal movement of the first linkage member will cause said first linkage member to disconnect from second linkage member.

9. For use in a modularized radio or autonomously controlled vehicle having two interconnectable modules, an actuating device mounted on the second of said two modules and a control element mounted on the first of said two modules, a separable control linkage assembly, comprising:

a first linkage member having a first coupling end and a second coupling end, said first coupling end operatively connectable to said actuating device;

a second linkage member having a first coupling end and a second coupling end, said first coupling end operatively connectable to said control element;

said second coupling end of said first linkage member and said second coupling end of said second linkage member are mutually magnetically attractive and separably connectable to one another by mutual magnetic attraction force for linking said first linkage member to said second linkage member to form one linkage assembly;

said mutual magnetic attraction force sustaining the connection of said first linkage member to said second linkage member having a strength sufficient for the linkage connection to withstand the linkage stress under allowed vehicle operation conditions without disconnection and to disconnect before the linkage parting stress reaches the level destructive to connected linkage members.

10. The separable control linkage assembly of 9, further comprising:

at least one guide member having an aperture through which one of said linkage members extends;

said aperture having the shape and size defining a limited transverse spatial region for said linkage member extending through said aperture while not obstructing linkage motion transmission, therefore forming a limited spatial region for said mutually magnetically attractive ends of said first and second linkage members, in which said mutually magnetically attractive ends are sufficiently close to one another to experience sufficient mutual magnetic attraction to result in connection of said first and second linkage members to form one linkage assembly.

11. The separable control linkage assembly of 10, further comprising:

a first structure, rigid, provided or extending from a predetermined location on said one linkage assembly;

a second structure, rigid, provided on or extended from said first module in physical relationship with said first structure forming a longitudinal movement limit for said one linkage assembly and therefore forming a limited operating range for said control element;

whereby, upon reaching said longitudinal movement limit said first structure is in physical contact with said second structure, thus preventing said one linkage assembly from further longitudinal movement, and further longitudinal movement of the first linkage member will cause said one linkage assembly to disconnect into said first linkage member and second linkage member.

12. The combination comprising:

(a) a modularized airplane having two interconnectable modules, the first module having a fuselage portion, at least one aerodynamically functional fin fixedly joined with said fuselage portion and a flight control surface having a control lever fixedly secured thereon movably attached to said fin, the second module having a fuselage portion complementary to the fuselage portion of said first module having support structures provided thereto, a set of operatively interconnected airplane flight components sufficient for airplane operation mounted on said support structures including at least one servo device;

(b) the separable control linkage of 10 for linking said servo device to said flight control surface;

(c) connection means for structurally connecting said first module and said second module to form an airplane, and for disassembling the airplane into separate said first module and said second module.

13. The combination of 12, wherein said set of interconnected airplane flight components further including a propulsion unit for providing thrust, electronics circuitry for controlling said servo device and said propulsion unit, a power supply means for powering onboard power consuming components including said servo device and said propulsion unit.

14. The combination of 12, wherein said connection means (c) comprising at least one pair of mutually magnetically attractive members connectable to one another by attracive magnetic force, affixed oppositely at predetermined locations on said first module and said second module for connecting said first module to said second module, having the magnetic force strength sufficient for the connection to withstand the stress under allowed airplane operation conditions without disconnection and to disconnect before the parting stress between connected modules reaches the level destructive to the connected modules.

15. The combination of 14, further comprising at least one set of two mutually physically matching and laterally interlocking structure sections provided oppositely at predetermined locations on said first module and said second module, adapted to be in mutually matching and interlocking position when said first module and said second module are interconnected, one of said two structure sections having a hollowed shape, wider at the opening, forming a physical acceptance for the other of said two structure sections for providing guidance for interconnecting said modules, and for preventing lateral relative movement between the connected modules.

16. The combination of 14, further comprising:

a first structure, rigid, provided or extending from a predetermined location on said one linkage assembly;

a second structure, rigid, provided in said first module in physical relationship with said first structure forming a longitudinal movement limit for said one linkage assembly and therefore forming a limited operating range for said control element;

whereby, upon reaching said longitudinal movement limit said first structure is in physical contact with said second structure, thus preventing said one linkage assembly from further longitudinal movement, and further longitudinal movement of the first linkage member will cause said first linkage member to disconnect from second linkage member.