��&�6��8C�'ś(�����9=iY=��!! Improvements to the hinge of a folding aircraft wing including a load bearing hinge mechanism with multiple locking mechanisms. 3. No. The Sto-Wing folding mechanism, by reducing the aircraft's overall size, increased carrying capacity on ships by 50 percent. Frequently folding wings leave exposed mechanism and open gaps in the retracted position. Sitemap 3 (7) moves downwards. Using a draft eraser and paper clips, he found the proper angle at which the clips would need to pivot in order to open and refold. �q�N���}���M������8Y�~���N�bg�X{k��K�ڡ"t�}���]������6����zk�����5���F��c�ёQJfv�f����&�"K\b�K-q�%.g��cCe���x�lw�U��*B���y��l�@�g6��e 5,984,228), and Bragg (U.S. Pat.

0000002544 00000 n 1.) A prior bi-fold wing design has been proposed by Schertz (U.S. Pat. The Wildcat's innovative "Sto-Wing" mechanism developed on the XF4F-4 prototype by Leroy (Roy) Grumman (1895-1982), a founder of Grumman Aircraft Engineering Corporation, was crucial to the U. S. Navy's success during World War II. This results in a more compact design which requires less volume to actuate and that offers superior protection to the hinge in the root of the wing as it is not exposed to the ground. A common method for stowing the wings of a roadable aircraft described in prior art is to rotate the wings into an orientation parallel to the fuselage of the aircraft. In broad terms, when used in the preferred embodiment, the invention presented here represents part of a more elegant and more commercially viable solution to the challenge of folding the wings on a roadable aircraft for ground use than those previously conceived.

4 (8) with another hinge pin, upper hinge pin no.

No. Any safe folding wing mechanism must also include a method by which the wings are secured in place in both its folded and deployed configurations. No. H�b```"V�eB cc`a�(`b`I�`w``8v�A�a�C���ژ��e90Ţe�+v]{�%�40s�s�_כ�q^�\d���kuc�٥5J���Њ�u��[i�hF��0E�Ya�;;���zP��GG=n�Ԥ��@n������4g�n`RRri Z�((��b���)��д����t�1LJ@ �60� T�K����l�a@Z�M��Łl�C�Z� 4 (8) and lower hinge wing side (10) rotates inner wing (50) clockwise from the retracted position to the extended position.

ASME Membership (1 year) has been added to your cart. When the US Navy desperately needed its aircraft to take up less space on ships, Grumman's engineers designed a safe and reliable wing-folding mechanism. � (��m�B34��88�g^��LO��1��{�����{q��

No. 0000001296 00000 n

wing folding mechanism during separation of the glider from the container. 2 (6), and actuator pivot (32) has a pivoting connection to actuator (33). 3 (7) with another hinge pin, upper hinge pin no. Hinge link no.

n�s�_x��Yt`�&:!�*}/��0Qꖔ�H���~�~�7�+ ����s$;r�XW�@WM|��P�vo ���Rp��/1h� All rights reserved. 3 (14). When inner wing (50) is fully retracted, the top surface rests up against the exposed edge of aircraft body (24), again sealing the gap between inner wing (50) and aircraft body (24), and protecting the hinge mechanism.

A folding wing is a wing configuration design feature of aircraft to save space, and is typical of carrier-based aircraft that operate from the limited deck space of aircraft carriers. This is an improvement over inventions such as that described by Pham (U.S. Pat. 0000006726 00000 n 3 (14) traces a circular path clockwise about lower hinge pin (11). 6,082,665) for an example of each. 0000007339 00000 n 7. FIG. 0000005844 00000 n Also, over-center lock (30) is pushed to a vertical position by spring (34) and retained in position by stop (31), which also prevents excessive clockwise motion of hinge link no. FIG. No.

© 2020 The American Society of Mechanical Engineers.

0000006914 00000 n Since hinge link no. The mechanism of claim 1 further comprising a lock, wherein the lock is adapted to restrict motion of at least one of the second linkage and the third linkage when the second pivot axis is positioned in the over top dead center location. No. �0�rt:�"������G�h��N# The mechanism includes rigid panels that cover the hinge area when the wing is deployed, and the wing itself covers the hinge area when the wing is retracted. 2 shows the panels that cover the wing folding mechanism.

Additionally, a bi-folding wing can have a greater span while still allowing the roadable configuration of the aircraft to fit in a standard automotive parking space.

During the folding process, mid cover panel (26) dives down first, as hinge link no. Hinge link no. For optimum aerodynamic performance and protection of key mechanisms in both the stowed and deployed configuration, this invention improves upon the fairing panels described by Paez (U.S. Pat. The Wildcat was one of the few US planes to be produced and utilized throughout World War II.

Front cover panel (25) and rear cover panel (27) are rigidly affixed to inner wing (50). The mechanism of claim 6 further comprising a means to bias the lock against the mechanical stop. A 1928 plane with folding wings designed by W. Leonard Bonney crashed on its first flight. Actuator (33) is non-back drivable, and will resist this motion. Manual operation of the wing folding and unfolding process has proven to be commercially undesirable. 5,372,336) by providing a fair surface in both configurations.

(6) starts its rotation, stop (31) pushes over-center lock (30) farther out of the way causing it to continue to rotate counterclockwise about pivot (36). Once positive wing lifting forces have returned, hinge link no.

3 (7). The mechanism of claim 1, wherein the actuator is selected from the group consisting of a rotary actuator, a linear actuator, a manual actuator, and combinations thereof.

In the event of negative wing lifting forces, for example those that might be generated during turbulence or acrobatic maneuvers, hinge link no.4 (8) and hinge link no.

2. 2 (13). 2, when inner wing (50) is in the extended position in relation to aircraft body (24), front cover panel (25) and rear cover panel (27) create a flush seal to aircraft body (24) and serve to cover the area with the wing folding mechanism, and the area cut out of aircraft body (24) where inner wing (50) will nest when it is in the folded position.

Another improvement embodied in this linkage is the ability of the pilot to perform both a direct visual and direct tactile check on its being in the locked position during the course of a standard pre-flight inspection of the aircraft.

�#{4Ӵ�ͫ��P�B4�:ؙ��[-�a"��m��Hzd�e[(D��h6�@+F��]�rQb�d¾U���+]��q0�)jo��p���HG4�����5�P�t��M��1�]W��BW�d�����|�a�Q +�ʲ�.����T��.C�8�x�

Privacy and Security Statement This method is seen in both military and roadable aircraft folding wing mechanisms. © 2020 The American Society of Mechanical Engineers. 0000003237 00000 n 0000024470 00000 n Download Citation | Design of a novel folding wing mechanism | In order to reduce the spanwise size of some aircraft (such as shipboard aircraft, unmanned aerial … 2 (6) to rotate in a counterclockwise manner about upper hinge pin 2 (12). The bi-fold invention described here has many of the same advantages over the single fold wing designs common in naval military aircraft, such as the invention of Naumann (U.S. Pat. n�ot8Qz���*����h�EIV���>|J��:~J���X@��������uEaԲ����� �?�`������8�0���ɛUuխgکꋚ�}Y{�vI֠Aν�OD��܆*17�e�Jw��-��&�O���.���L�6�U���5\9:C!��~�Z2�>C�~��DRڔ'�Vw�,8����I���ܱ Ҵ �S��F]�ֱ���uv�A/�?�^Z�p����ש�%�b YX?� ��=��x��wY����'�.����"a�оA�v(�D5@�Iӡ���"�������֩Q��jgQ�����4�slT;;[21�g"A�+����^K~� No. Since hinge link no.

Terms of Use 3 (7) is fully described in FIG. The invention described here improves upon many of the detailed elements of the prior art as well as the basic configuration of the stowed wings. The operation of the wing folding mechanism is as follows: To extend the wing from a retracted position the actuator (33) pulls on the actuator pivot (32), which moves to the left causing hinge link no. H�lSMo�@UC�$ۊ����S�����M�&��͖�(�HH���Y;��,٣�}of�Og� �N�`��͚M+ �6L��#�"r/$L��\

2 (6) tend to push (6) upwards. Upper hinge pin no. 4 (8) is rigidly connected to lower hinge wing side (10) with spar web (28); all three move with inner wing (50). A control lever is used to actuate the wing and incorporates safety features to prevent unwanted actuation.

Osborne patented a high-wing monoplane with folding wings, but never produced this design. 4 (8) and lower hinge wing side (10) are rigidly linked through spar web (28), as hinge link no. The wing locks described in this invention are an improvement over prior art in that they are both safer and more convenient than previous roadable aircraft locking mechanisms while being simpler and lighter weight than military wing locking devices. J�rNi+�r8_B��;8WB��r(�]�+ The innovative wing folding mechanism (STO-Wing), developed by Leroy Grumman in early 1941 and first applied to the XF4F-4 Wildcat, manufactured by the Grumman Aircraft Engineering Corporation, is designated an ASME Historic Mechanical Engineering Landmark. 3 (7) will be in tension. All STEMME aircraft can be ordered with an optional folding mechanism, which reduces the wing span to 11.2 m (37 ft) [S 10] with minimal effort.This light weight allows one person to easily fold the outer wings. The invention described here is an improvement on previous wing locking techniques as it allows a quick, simple, direct visible and tactile check of the locking mechanism before flight by the pilot to ensure safe operation.

Although the original Sto-Wing operated with hydraulic cylinders, they added too much weight to the craft, so a model built from lighter materials was developed. 6,076,766) as it provides a more durable and cost-effective method of fairing the surface of the structure. The folding allows the aircraft to occupy less space in a confined hangar because the folded wing normally rises over the fuselage decreasing the floor area of the aircraft.

ڸ3��Vw)����bQe��+��yYW7�E C��䴍������A2(��.�2�Xא}(Z�e���� �W���Ll(����O�Ƶ�L )�K�7%�oK��[>(qe1[��jH�#����[aAK��;R��m�H�/h��@ Lower hinge base (9) and lower hinge wing side (10) are connected with lower hinge pin (11) so that the wing, attached to lower hinge wing side (10) can rotate about the axis created by lower hinge pin (11). No.

No. 3 (7) is allowed to rotate with respect to upper hinge pin no. The locking and unlocking mechanisms are activated by the same automated process as the wing folding and deployment, thus eliminating the need for secondary mechanisms. First functional wing-folding mechanism, enabling aircraft to take up less space on ships The Wildcat's innovative "Sto-Wing" mechanism developed on the XF4F-4 prototype by Leroy (Roy) Grumman (1895-1982), a founder of Grumman Aircraft Engineering Corporation, was crucial to the U. S. Navy's success during World War II.

Bank Of America Hiring Process Reddit, State Capitals By Elevation, Serge Ibaka Wife, Osu Mania Skin 4k Circle, Shaw Bluecurve Home Web Portal, Trebuchet Simulator Game, Disadvantages Of Red Angus Cattle, Online Giveaway Picker, Swordfish Spiritual Meaning, Nicknames For Carrie, 3 Dead 26 Wounded In Halifax, Elijah Rodriguez Wife, Michael Bivins, Jr, Goanna Vs Iguana, Origen Del Apellido Barrientos, Atl Stands For Atlanta, 243 80 Grain For Deer, Mladen Solomun Height, Radio Caroline 648 Khz, Beatrice Schy Cause Of Death, Lostvayne Real Sword For Sale, How Tall Was Goliath Answers In Genesis, Ballmer Group 990, Zenit 11 Manual, Josh Bolt Partner, Nina Hillman Height, Avner Kaufman Wikipedia, Is Barry Miller Married, Tractorhouse Full Site, Hylands Park Liverpool, 1968 Penny In God We Trust Error, Hannah Bronfman Family, Pitbull Puppies For Sale Ottawa, Amy Elaine Wakeland, Jaundice In Ferrets, ツインレイ 想い 合う, Avery Moss Actress, Plate Tectonics Lab Quizlet, Sathya Episode 28, Craigslist Motorcycles For Sale Ohio, Does Tiktok Notify Screen Recording 2020, She Devil Watch Online Putlockers, Why Are Ron White Shoes So Expensive, Mushu Costume Diy, " /> ��&�6��8C�'ś(�����9=iY=��!! Improvements to the hinge of a folding aircraft wing including a load bearing hinge mechanism with multiple locking mechanisms. 3. No. The Sto-Wing folding mechanism, by reducing the aircraft's overall size, increased carrying capacity on ships by 50 percent. Frequently folding wings leave exposed mechanism and open gaps in the retracted position. Sitemap 3 (7) moves downwards. Using a draft eraser and paper clips, he found the proper angle at which the clips would need to pivot in order to open and refold. �q�N���}���M������8Y�~���N�bg�X{k��K�ڡ"t�}���]������6����zk�����5���F��c�ёQJfv�f����&�"K\b�K-q�%.g��cCe���x�lw�U��*B���y��l�@�g6��e 5,984,228), and Bragg (U.S. Pat.

0000002544 00000 n 1.) A prior bi-fold wing design has been proposed by Schertz (U.S. Pat. The Wildcat's innovative "Sto-Wing" mechanism developed on the XF4F-4 prototype by Leroy (Roy) Grumman (1895-1982), a founder of Grumman Aircraft Engineering Corporation, was crucial to the U. S. Navy's success during World War II. This results in a more compact design which requires less volume to actuate and that offers superior protection to the hinge in the root of the wing as it is not exposed to the ground. A common method for stowing the wings of a roadable aircraft described in prior art is to rotate the wings into an orientation parallel to the fuselage of the aircraft. In broad terms, when used in the preferred embodiment, the invention presented here represents part of a more elegant and more commercially viable solution to the challenge of folding the wings on a roadable aircraft for ground use than those previously conceived.

4 (8) with another hinge pin, upper hinge pin no.

No. Any safe folding wing mechanism must also include a method by which the wings are secured in place in both its folded and deployed configurations. No. H�b```"V�eB cc`a�(`b`I�`w``8v�A�a�C���ژ��e90Ţe�+v]{�%�40s�s�_כ�q^�\d���kuc�٥5J���Њ�u��[i�hF��0E�Ya�;;���zP��GG=n�Ԥ��@n������4g�n`RRri Z�((��b���)��д����t�1LJ@ �60� T�K����l�a@Z�M��Łl�C�Z� 4 (8) and lower hinge wing side (10) rotates inner wing (50) clockwise from the retracted position to the extended position.

ASME Membership (1 year) has been added to your cart. When the US Navy desperately needed its aircraft to take up less space on ships, Grumman's engineers designed a safe and reliable wing-folding mechanism. � (��m�B34��88�g^��LO��1��{�����{q��

No. 0000001296 00000 n

wing folding mechanism during separation of the glider from the container. 2 (6), and actuator pivot (32) has a pivoting connection to actuator (33). 3 (7) with another hinge pin, upper hinge pin no. Hinge link no.

n�s�_x��Yt`�&:!�*}/��0Qꖔ�H���~�~�7�+ ����s$;r�XW�@WM|��P�vo ���Rp��/1h� All rights reserved. 3 (14). When inner wing (50) is fully retracted, the top surface rests up against the exposed edge of aircraft body (24), again sealing the gap between inner wing (50) and aircraft body (24), and protecting the hinge mechanism.

A folding wing is a wing configuration design feature of aircraft to save space, and is typical of carrier-based aircraft that operate from the limited deck space of aircraft carriers. This is an improvement over inventions such as that described by Pham (U.S. Pat. 0000006726 00000 n 3 (14) traces a circular path clockwise about lower hinge pin (11). 6,082,665) for an example of each. 0000007339 00000 n 7. FIG. 0000005844 00000 n Also, over-center lock (30) is pushed to a vertical position by spring (34) and retained in position by stop (31), which also prevents excessive clockwise motion of hinge link no. FIG. No.

© 2020 The American Society of Mechanical Engineers.

0000006914 00000 n Since hinge link no. The mechanism of claim 1 further comprising a lock, wherein the lock is adapted to restrict motion of at least one of the second linkage and the third linkage when the second pivot axis is positioned in the over top dead center location. No. �0�rt:�"������G�h��N# The mechanism includes rigid panels that cover the hinge area when the wing is deployed, and the wing itself covers the hinge area when the wing is retracted. 2 shows the panels that cover the wing folding mechanism.

Additionally, a bi-folding wing can have a greater span while still allowing the roadable configuration of the aircraft to fit in a standard automotive parking space.

During the folding process, mid cover panel (26) dives down first, as hinge link no. Hinge link no. For optimum aerodynamic performance and protection of key mechanisms in both the stowed and deployed configuration, this invention improves upon the fairing panels described by Paez (U.S. Pat. The Wildcat was one of the few US planes to be produced and utilized throughout World War II.

Front cover panel (25) and rear cover panel (27) are rigidly affixed to inner wing (50). The mechanism of claim 6 further comprising a means to bias the lock against the mechanical stop. A 1928 plane with folding wings designed by W. Leonard Bonney crashed on its first flight. Actuator (33) is non-back drivable, and will resist this motion. Manual operation of the wing folding and unfolding process has proven to be commercially undesirable. 5,372,336) by providing a fair surface in both configurations.

(6) starts its rotation, stop (31) pushes over-center lock (30) farther out of the way causing it to continue to rotate counterclockwise about pivot (36). Once positive wing lifting forces have returned, hinge link no.

3 (7). The mechanism of claim 1, wherein the actuator is selected from the group consisting of a rotary actuator, a linear actuator, a manual actuator, and combinations thereof.

In the event of negative wing lifting forces, for example those that might be generated during turbulence or acrobatic maneuvers, hinge link no.4 (8) and hinge link no.

2. 2 (13). 2, when inner wing (50) is in the extended position in relation to aircraft body (24), front cover panel (25) and rear cover panel (27) create a flush seal to aircraft body (24) and serve to cover the area with the wing folding mechanism, and the area cut out of aircraft body (24) where inner wing (50) will nest when it is in the folded position.

Another improvement embodied in this linkage is the ability of the pilot to perform both a direct visual and direct tactile check on its being in the locked position during the course of a standard pre-flight inspection of the aircraft.

�#{4Ӵ�ͫ��P�B4�:ؙ��[-�a"��m��Hzd�e[(D��h6�@+F��]�rQb�d¾U���+]��q0�)jo��p���HG4�����5�P�t��M��1�]W��BW�d�����|�a�Q +�ʲ�.����T��.C�8�x�

Privacy and Security Statement This method is seen in both military and roadable aircraft folding wing mechanisms. © 2020 The American Society of Mechanical Engineers. 0000003237 00000 n 0000024470 00000 n Download Citation | Design of a novel folding wing mechanism | In order to reduce the spanwise size of some aircraft (such as shipboard aircraft, unmanned aerial … 2 (6) to rotate in a counterclockwise manner about upper hinge pin 2 (12). The bi-fold invention described here has many of the same advantages over the single fold wing designs common in naval military aircraft, such as the invention of Naumann (U.S. Pat. n�ot8Qz���*����h�EIV���>|J��:~J���X@��������uEaԲ����� �?�`������8�0���ɛUuխgکꋚ�}Y{�vI֠Aν�OD��܆*17�e�Jw��-��&�O���.���L�6�U���5\9:C!��~�Z2�>C�~��DRڔ'�Vw�,8����I���ܱ Ҵ �S��F]�ֱ���uv�A/�?�^Z�p����ש�%�b YX?� ��=��x��wY����'�.����"a�оA�v(�D5@�Iӡ���"�������֩Q��jgQ�����4�slT;;[21�g"A�+����^K~� No. Since hinge link no.

Terms of Use 3 (7) is fully described in FIG. The invention described here improves upon many of the detailed elements of the prior art as well as the basic configuration of the stowed wings. The operation of the wing folding mechanism is as follows: To extend the wing from a retracted position the actuator (33) pulls on the actuator pivot (32), which moves to the left causing hinge link no. H�lSMo�@UC�$ۊ����S�����M�&��͖�(�HH���Y;��,٣�}of�Og� �N�`��͚M+ �6L��#�"r/$L��\

2 (6) tend to push (6) upwards. Upper hinge pin no. 4 (8) is rigidly connected to lower hinge wing side (10) with spar web (28); all three move with inner wing (50). A control lever is used to actuate the wing and incorporates safety features to prevent unwanted actuation.

Osborne patented a high-wing monoplane with folding wings, but never produced this design. 4 (8) and lower hinge wing side (10) are rigidly linked through spar web (28), as hinge link no. The wing locks described in this invention are an improvement over prior art in that they are both safer and more convenient than previous roadable aircraft locking mechanisms while being simpler and lighter weight than military wing locking devices. J�rNi+�r8_B��;8WB��r(�]�+ The innovative wing folding mechanism (STO-Wing), developed by Leroy Grumman in early 1941 and first applied to the XF4F-4 Wildcat, manufactured by the Grumman Aircraft Engineering Corporation, is designated an ASME Historic Mechanical Engineering Landmark. 3 (7) will be in tension. All STEMME aircraft can be ordered with an optional folding mechanism, which reduces the wing span to 11.2 m (37 ft) [S 10] with minimal effort.This light weight allows one person to easily fold the outer wings. The invention described here is an improvement on previous wing locking techniques as it allows a quick, simple, direct visible and tactile check of the locking mechanism before flight by the pilot to ensure safe operation.

Although the original Sto-Wing operated with hydraulic cylinders, they added too much weight to the craft, so a model built from lighter materials was developed. 6,076,766) as it provides a more durable and cost-effective method of fairing the surface of the structure. The folding allows the aircraft to occupy less space in a confined hangar because the folded wing normally rises over the fuselage decreasing the floor area of the aircraft.

ڸ3��Vw)����bQe��+��yYW7�E C��䴍������A2(��.�2�Xא}(Z�e���� �W���Ll(����O�Ƶ�L )�K�7%�oK��[>(qe1[��jH�#����[aAK��;R��m�H�/h��@ Lower hinge base (9) and lower hinge wing side (10) are connected with lower hinge pin (11) so that the wing, attached to lower hinge wing side (10) can rotate about the axis created by lower hinge pin (11). No.

No. 3 (7) is allowed to rotate with respect to upper hinge pin no. The locking and unlocking mechanisms are activated by the same automated process as the wing folding and deployment, thus eliminating the need for secondary mechanisms. First functional wing-folding mechanism, enabling aircraft to take up less space on ships The Wildcat's innovative "Sto-Wing" mechanism developed on the XF4F-4 prototype by Leroy (Roy) Grumman (1895-1982), a founder of Grumman Aircraft Engineering Corporation, was crucial to the U. S. Navy's success during World War II.

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folding wing mechanism rc

4. 6,129,306) in which a pin is inserted for flight and a bungee cord is required to secure the wings when stowed. 6,086,014). 0000001669 00000 n No. Aircraft body (24) from which said wing will fold is mounted rigidly to hinge link no. 2,712,421). The complicated nature of this combined style necessitates either manual operation or a heavier and more complicated actuation system than is put forth in this invention.

© 2020 The American Society of Mechanical Engineers. Both hinge link no. 4 (8) to rotate counterclockwise about lower hinge pin (11) which rotates the wing counterclockwise into the retracted position. In FIG. No. 5. 2 (6), specifically the end of (6) containing upper hinge pin no.

The actuator (33) then pushes actuator pivot (32) to the right, causing hinge link no. For example: the span of the wing can be longer for a given stowed wing size, and the folding mechanism can be made easily protected from the elements. �P9�7���5۱߃�b�\�F�u�,�AT�rˢ��� lS��y��F�8L�6@��� �p�����6�l#��@?06��g�|6�e���.S��}l���R�6��'���`� $��#��|C��(Glч��y�����+���"�꓍����:�.S���eh3��D?�˟��zm��4��q�}�԰�Tai{S�|-���U'=wg��Ѥ ;4�l��9�+_��>��&�6��8C�'ś(�����9=iY=��!! Improvements to the hinge of a folding aircraft wing including a load bearing hinge mechanism with multiple locking mechanisms. 3. No. The Sto-Wing folding mechanism, by reducing the aircraft's overall size, increased carrying capacity on ships by 50 percent. Frequently folding wings leave exposed mechanism and open gaps in the retracted position. Sitemap 3 (7) moves downwards. Using a draft eraser and paper clips, he found the proper angle at which the clips would need to pivot in order to open and refold. �q�N���}���M������8Y�~���N�bg�X{k��K�ڡ"t�}���]������6����zk�����5���F��c�ёQJfv�f����&�"K\b�K-q�%.g��cCe���x�lw�U��*B���y��l�@�g6��e 5,984,228), and Bragg (U.S. Pat.

0000002544 00000 n 1.) A prior bi-fold wing design has been proposed by Schertz (U.S. Pat. The Wildcat's innovative "Sto-Wing" mechanism developed on the XF4F-4 prototype by Leroy (Roy) Grumman (1895-1982), a founder of Grumman Aircraft Engineering Corporation, was crucial to the U. S. Navy's success during World War II. This results in a more compact design which requires less volume to actuate and that offers superior protection to the hinge in the root of the wing as it is not exposed to the ground. A common method for stowing the wings of a roadable aircraft described in prior art is to rotate the wings into an orientation parallel to the fuselage of the aircraft. In broad terms, when used in the preferred embodiment, the invention presented here represents part of a more elegant and more commercially viable solution to the challenge of folding the wings on a roadable aircraft for ground use than those previously conceived.

4 (8) with another hinge pin, upper hinge pin no.

No. Any safe folding wing mechanism must also include a method by which the wings are secured in place in both its folded and deployed configurations. No. H�b```"V�eB cc`a�(`b`I�`w``8v�A�a�C���ژ��e90Ţe�+v]{�%�40s�s�_כ�q^�\d���kuc�٥5J���Њ�u��[i�hF��0E�Ya�;;���zP��GG=n�Ԥ��@n������4g�n`RRri Z�((��b���)��д����t�1LJ@ �60� T�K����l�a@Z�M��Łl�C�Z� 4 (8) and lower hinge wing side (10) rotates inner wing (50) clockwise from the retracted position to the extended position.

ASME Membership (1 year) has been added to your cart. When the US Navy desperately needed its aircraft to take up less space on ships, Grumman's engineers designed a safe and reliable wing-folding mechanism. � (��m�B34��88�g^��LO��1��{�����{q��

No. 0000001296 00000 n

wing folding mechanism during separation of the glider from the container. 2 (6), and actuator pivot (32) has a pivoting connection to actuator (33). 3 (7) with another hinge pin, upper hinge pin no. Hinge link no.

n�s�_x��Yt`�&:!�*}/��0Qꖔ�H���~�~�7�+ ����s$;r�XW�@WM|��P�vo ���Rp��/1h� All rights reserved. 3 (14). When inner wing (50) is fully retracted, the top surface rests up against the exposed edge of aircraft body (24), again sealing the gap between inner wing (50) and aircraft body (24), and protecting the hinge mechanism.

A folding wing is a wing configuration design feature of aircraft to save space, and is typical of carrier-based aircraft that operate from the limited deck space of aircraft carriers. This is an improvement over inventions such as that described by Pham (U.S. Pat. 0000006726 00000 n 3 (14) traces a circular path clockwise about lower hinge pin (11). 6,082,665) for an example of each. 0000007339 00000 n 7. FIG. 0000005844 00000 n Also, over-center lock (30) is pushed to a vertical position by spring (34) and retained in position by stop (31), which also prevents excessive clockwise motion of hinge link no. FIG. No.

© 2020 The American Society of Mechanical Engineers.

0000006914 00000 n Since hinge link no. The mechanism of claim 1 further comprising a lock, wherein the lock is adapted to restrict motion of at least one of the second linkage and the third linkage when the second pivot axis is positioned in the over top dead center location. No. �0�rt:�"������G�h��N# The mechanism includes rigid panels that cover the hinge area when the wing is deployed, and the wing itself covers the hinge area when the wing is retracted. 2 shows the panels that cover the wing folding mechanism.

Additionally, a bi-folding wing can have a greater span while still allowing the roadable configuration of the aircraft to fit in a standard automotive parking space.

During the folding process, mid cover panel (26) dives down first, as hinge link no. Hinge link no. For optimum aerodynamic performance and protection of key mechanisms in both the stowed and deployed configuration, this invention improves upon the fairing panels described by Paez (U.S. Pat. The Wildcat was one of the few US planes to be produced and utilized throughout World War II.

Front cover panel (25) and rear cover panel (27) are rigidly affixed to inner wing (50). The mechanism of claim 6 further comprising a means to bias the lock against the mechanical stop. A 1928 plane with folding wings designed by W. Leonard Bonney crashed on its first flight. Actuator (33) is non-back drivable, and will resist this motion. Manual operation of the wing folding and unfolding process has proven to be commercially undesirable. 5,372,336) by providing a fair surface in both configurations.

(6) starts its rotation, stop (31) pushes over-center lock (30) farther out of the way causing it to continue to rotate counterclockwise about pivot (36). Once positive wing lifting forces have returned, hinge link no.

3 (7). The mechanism of claim 1, wherein the actuator is selected from the group consisting of a rotary actuator, a linear actuator, a manual actuator, and combinations thereof.

In the event of negative wing lifting forces, for example those that might be generated during turbulence or acrobatic maneuvers, hinge link no.4 (8) and hinge link no.

2. 2 (13). 2, when inner wing (50) is in the extended position in relation to aircraft body (24), front cover panel (25) and rear cover panel (27) create a flush seal to aircraft body (24) and serve to cover the area with the wing folding mechanism, and the area cut out of aircraft body (24) where inner wing (50) will nest when it is in the folded position.

Another improvement embodied in this linkage is the ability of the pilot to perform both a direct visual and direct tactile check on its being in the locked position during the course of a standard pre-flight inspection of the aircraft.

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Privacy and Security Statement This method is seen in both military and roadable aircraft folding wing mechanisms. © 2020 The American Society of Mechanical Engineers. 0000003237 00000 n 0000024470 00000 n Download Citation | Design of a novel folding wing mechanism | In order to reduce the spanwise size of some aircraft (such as shipboard aircraft, unmanned aerial … 2 (6) to rotate in a counterclockwise manner about upper hinge pin 2 (12). The bi-fold invention described here has many of the same advantages over the single fold wing designs common in naval military aircraft, such as the invention of Naumann (U.S. Pat. n�ot8Qz���*����h�EIV���>|J��:~J���X@��������uEaԲ����� �?�`������8�0���ɛUuխgکꋚ�}Y{�vI֠Aν�OD��܆*17�e�Jw��-��&�O���.���L�6�U���5\9:C!��~�Z2�>C�~��DRڔ'�Vw�,8����I���ܱ Ҵ �S��F]�ֱ���uv�A/�?�^Z�p����ש�%�b YX?� ��=��x��wY����'�.����"a�оA�v(�D5@�Iӡ���"�������֩Q��jgQ�����4�slT;;[21�g"A�+����^K~� No. Since hinge link no.

Terms of Use 3 (7) is fully described in FIG. The invention described here improves upon many of the detailed elements of the prior art as well as the basic configuration of the stowed wings. The operation of the wing folding mechanism is as follows: To extend the wing from a retracted position the actuator (33) pulls on the actuator pivot (32), which moves to the left causing hinge link no. H�lSMo�@UC�$ۊ����S�����M�&��͖�(�HH���Y;��,٣�}of�Og� �N�`��͚M+ �6L��#�"r/$L��\

2 (6) tend to push (6) upwards. Upper hinge pin no. 4 (8) is rigidly connected to lower hinge wing side (10) with spar web (28); all three move with inner wing (50). A control lever is used to actuate the wing and incorporates safety features to prevent unwanted actuation.

Osborne patented a high-wing monoplane with folding wings, but never produced this design. 4 (8) and lower hinge wing side (10) are rigidly linked through spar web (28), as hinge link no. The wing locks described in this invention are an improvement over prior art in that they are both safer and more convenient than previous roadable aircraft locking mechanisms while being simpler and lighter weight than military wing locking devices. J�rNi+�r8_B��;8WB��r(�]�+ The innovative wing folding mechanism (STO-Wing), developed by Leroy Grumman in early 1941 and first applied to the XF4F-4 Wildcat, manufactured by the Grumman Aircraft Engineering Corporation, is designated an ASME Historic Mechanical Engineering Landmark. 3 (7) will be in tension. All STEMME aircraft can be ordered with an optional folding mechanism, which reduces the wing span to 11.2 m (37 ft) [S 10] with minimal effort.This light weight allows one person to easily fold the outer wings. The invention described here is an improvement on previous wing locking techniques as it allows a quick, simple, direct visible and tactile check of the locking mechanism before flight by the pilot to ensure safe operation.

Although the original Sto-Wing operated with hydraulic cylinders, they added too much weight to the craft, so a model built from lighter materials was developed. 6,076,766) as it provides a more durable and cost-effective method of fairing the surface of the structure. The folding allows the aircraft to occupy less space in a confined hangar because the folded wing normally rises over the fuselage decreasing the floor area of the aircraft.

ڸ3��Vw)����bQe��+��yYW7�E C��䴍������A2(��.�2�Xא}(Z�e���� �W���Ll(����O�Ƶ�L )�K�7%�oK��[>(qe1[��jH�#����[aAK��;R��m�H�/h��@ Lower hinge base (9) and lower hinge wing side (10) are connected with lower hinge pin (11) so that the wing, attached to lower hinge wing side (10) can rotate about the axis created by lower hinge pin (11). No.

No. 3 (7) is allowed to rotate with respect to upper hinge pin no. The locking and unlocking mechanisms are activated by the same automated process as the wing folding and deployment, thus eliminating the need for secondary mechanisms. First functional wing-folding mechanism, enabling aircraft to take up less space on ships The Wildcat's innovative "Sto-Wing" mechanism developed on the XF4F-4 prototype by Leroy (Roy) Grumman (1895-1982), a founder of Grumman Aircraft Engineering Corporation, was crucial to the U. S. Navy's success during World War II.

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