Foldable arm mechanism for rotary wing aircraft
A folding device is disclosed for a rotary wing aircraft. The foldable device includes a plurality of pivots mounting a plurality of arms supporting driven propellers of the rotary wing aircraft. A projection and a detent resiliently cooperate for securing each of the plurality of arms in desired orientations relative to the rotary wing aircraft and for enabling each of the plurality of arms to rotate about the pivot into a folded position.
1. A folding device for an aircraft, comprising:
an aircraft frame having a horizontal surface;
a frame pivot aperture defined in said horizontal surface of said aircraft frame;
an arm extending between an inner end and an outer end;
an arm pivot aperture located in said inner end of said arm;
said outer end of said arm adapted to mount a driven propeller;
a pivot extending through said frame pivot aperture and said arm pivot aperture for pivotably mounting said arm to said aircraft frame;
a projection extending from one of said aircraft frame and said arm;
a detent located on the other of said aircraft frame and said arm;
a resilient mounting for mounting one of said detent and said projection for enabling said projection to resiliently engage said detent for securing said arm in a desired orientation relative to said aircraft frame and for enabling said arm to rotate about said pivot into a folded position upon intentional folding for transportation or storage or folded as a result of an undesired collision or landing of the rotary wing aircraft;
said horizontal surface of said aircraft frame defining a frame support extending from a proximal end to a distal end; and
said projection extends from said distal end of said frame support.
2. A folding device as set forth in claim 1 , wherein said projection extends from said aircraft frame and said detent is defined in said arm.
3. A folding device for an aircraft, comprising:
an aircraft frame having a horizontal surface;
a frame pivot aperture defined in said horizontal surface of said aircraft frame;
an arm extending between an inner end and an outer end;
an arm pivot aperture located in said inner end of said arm;
said outer end of said arm adapted to mount a driven propeller;
a pivot extending through said frame pivot aperture and said arm pivot aperture for pivotably mounting said arm to said aircraft frame;
a projection extending from one of said aircraft frame and said arm;
a detent located on the other of said aircraft frame and said arm;
a resilient mounting for mounting one of said detent and said projection for enabling said projection to resiliently engage said detent for securing said arm in a desired orientation relative to said aircraft frame and for enabling said arm to rotate about said pivot into a folded position;
a U-shaped slot located in said horizontal surface of said aircraft frame defining a frame support extending from a proximal end to a distal end; and
said distal end of said frame support made flexible for defining said resilient mounting.
4. A folding device as set forth in claim 3 , wherein said frame support is integral with said aircraft frame as a one-piece unit.
5. A folding device as set forth in claim 1 , wherein the frame is made of carbon fiber structure.
6. A folding device for an aircraft, comprising:
an aircraft frame having a horizontal surface;
a frame pivot aperture defined in said horizontal surface of said aircraft frame;
an arm extending between an inner end and an outer end;
an arm pivot aperture located in said inner end of said arm;
said outer end of said arm adapted to mount a driven propeller;
a pivot extending through said frame pivot aperture and said arm pivot aperture for pivotably mounting said arm to said aircraft frame;
a projection extending from one of said aircraft frame and said arm;
a detent located on the other of said aircraft frame and said arm; and
a resilient mounting for mounting one of said detent and said projection for enabling said projection to resiliently engage said detent for securing said arm in a desired orientation relative to said aircraft frame and for enabling said arm to rotate about said pivot into a folded position upon intentional folding for transportation or storage or folded as a result of an undesired collision or landing of the rotary wing aircraft;
a U-shaped slot located in said horizontal surface of said aircraft frame defining a frame support extending from a proximal end to a distal end;
said U-shaped slot being formed from a material to establishes said distal end of said frame support for defining said resilient mounting; and
said projection extending from said distal end of said frame support.
7. A folding device as set forth in claim 1 , wherein said detent is defined in said inner end of said arm; and
an arcuate recess disposed adjacent to said detent for facilitating rotation of said arm about said pivot.
8. A folding device as set forth in claim 1 , wherein said detent is defined in said inner end of said arm; and
a first and a second arcuate recess disposed on opposed sides of said detent for facilitating rotation of said arm about said pivot.
9. A folding device as set forth in claim 1 , including a detent plate for defining said detent.