WO2017001898A1 - Multi-functional mission grip system for a vehicle - Google Patents

Multi-functional mission grip system for a vehicle Download PDF

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Publication number
WO2017001898A1
WO2017001898A1 PCT/IB2015/054954 IB2015054954W WO2017001898A1 WO 2017001898 A1 WO2017001898 A1 WO 2017001898A1 IB 2015054954 W IB2015054954 W IB 2015054954W WO 2017001898 A1 WO2017001898 A1 WO 2017001898A1
Authority
WO
WIPO (PCT)
Prior art keywords
mission
grip
grips
control
copilot
Prior art date
Application number
PCT/IB2015/054954
Other languages
French (fr)
Inventor
Yuksel SERDAR
Dincer CALISLAR
Samet KARAKAS
Ulas ARSLAN
Savas KUS
Ugur Selim GENCOGLU
Umur AKINCI
Serkan DORTKARDESLER
Ahmet Coban
Ahmet MERT
Ahmet Hakan SEZGIN
Original Assignee
Aselsan Elektronik Sanayi Ve Ticaret Anonim Sirketi
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aselsan Elektronik Sanayi Ve Ticaret Anonim Sirketi filed Critical Aselsan Elektronik Sanayi Ve Ticaret Anonim Sirketi
Priority to PL421909A priority Critical patent/PL421909A1/en
Priority to TN2017000151A priority patent/TN2017000151A1/en
Publication of WO2017001898A1 publication Critical patent/WO2017001898A1/en
Priority to ZA2017/02383A priority patent/ZA201702383B/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/22—Aiming or laying means for vehicle-borne armament, e.g. on aircraft
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05G—CONTROL DEVICES OR SYSTEMS INSOFAR AS CHARACTERISED BY MECHANICAL FEATURES ONLY
    • G05G9/00—Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously
    • G05G9/02—Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only
    • G05G9/04—Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously
    • G05G9/047—Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
    • G05G9/04785—Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks the controlling member being the operating part of a switch arrangement
    • G05G9/04788—Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks the controlling member being the operating part of a switch arrangement comprising additional control elements

Definitions

  • the present invention relates to a mission grip system which enables to control moving digital map system, weapon system and target detection/sighting system equipment by means of a copilot right hand mission grip, copilot left hand mission grip, pilot mission grip and control units integrated into aircrafts (e.g. T-129 Atak (Attack) helicopter).
  • a copilot right hand mission grip e.g. copilot left hand mission grip
  • pilot mission grip e.g. T-129 Atak (Attack) helicopter.
  • the interfaces between the user and the moving digital map system, weapon system and target detection/sighting system can be provided by limited means, and time consuming methods that are difficult to be accessed.
  • the number of the systems controlled by the mission grips used in aircrafts is limited and/or they are more inconvenient. This in turn increases the user' s time loss and error rate.
  • the objective of the present invention is to provide a mission grip system which enables the user to control different systems simultaneously in aircrafts. Thanks to the present invention, a more convenient accessibility is provided between the pilots and the moving digital map system, weapon system and target detection/sighting system, and by the support of more user interfaces, the pilots are enabled to save time and the error rate is reduced.
  • Another objective of the present invention is to provide a mission grip system which, in addition to providing ease of use in short and long duration flights of the users by means of its ergonomic design architecture, provides advantage of space for the other equipment in the cockpit owing to the fact that it occupies a smaller space in the cockpit.
  • the labels indicating the key functions can be read in night flights and the said mission equipment are enabled to be used more effectively in night conditions compared to the past.
  • the mission grip system of the present invention is developed in compliance with the environmental requirements determined by military standards (MIL-HDBK- 5400, MIL-STD-810, MIL-STD-704 and MIL-STD-461). Within this framework, altitude, low and high temperature, thermal shock, humidity, vibration, mechanical shock, dust, salty atmosphere, rain, acceleration, solar radiation, temperature-altitude, temperature-vibration, power and EMI/EMC tests are applied to the equipment.
  • Figure 1 is the schematic view of the mission grip system.
  • Figure 2 is a perspective view of the pilot mission grip.
  • Figure 3 is a perspective view of the button guard on the gun/missile fire trigger.
  • Figure 4 is a side view of the button guard on the gun/missile fire trigger.
  • Figure 5 is a perspective view of the button guard on the laser fire trigger.
  • Figure 6 is a view of the sunk button in the mission grip.
  • Figure 7 is a perspective view of the first protrusions and the second protrusion in the mission grip.
  • Figure 8 is a perspective view of the copilot left hand and right hand mission grips.
  • Figure 9 is a front perspective view of the control unit.
  • Figure 10 is a rear perspective view of the control unit.
  • Control unit A mission grip system (1) which enables the pilot/copilot to control the critical mission equipment in aircrafts simultaneously, basically comprises at least one pilot mission grip (2),
  • At least one fire trigger (5) which enables to fire the gun, missile and/or laser located in the aircraft,
  • At least one button guard (6) which prevents accidental pressing of the fire trigger (5) by covering the said trigger
  • At least one sunk button (7) which is assigned for critical missions and which is sunk in at least one of the mission grips,
  • At least one first protrusion (8) which is provided on at least one of the mission grips and which prevents slipping of the user's hand from the mission grip by providing a friction between the hand and the handle
  • at least one second protrusion (9) which is provided at the base of at least one of the mission grips and which contacts the bottom of the hand and extends outwards preferably parallel to the ground plane for preventing the hand from slipping downwards
  • At least one gun interface unit (10) which is adapted to generate control signals according to the discrete control and condition signals coming from the mission grips for controlling and firing the gun units in the aircraft and to transmit these signals to the gun unit that will be controlled; and to generate location information from the data coming from the gun unit location sensors and to transmit these information to the gun unit that will be directed,
  • At least one weapon interface unit (11) which is adapted to generate the power and discrete signals required to fire the laser guided missiles, unguided missiles, air-to-air missiles and/or antitank missiles which are integrated to the aircraft,
  • At least one mission computer (12) which is adapted to control all mission equipment such as moving digital map system, weapon system and target detection/sighting system of the aircraft and to provide the data transmission between the said equipment, control levers (collective & cyclic) (13) which enable to perform the basic flight controls,
  • mission equipment such as moving digital map system, weapon system and target detection/sighting system of the aircraft and to provide the data transmission between the said equipment, control levers (collective & cyclic) (13) which enable to perform the basic flight controls,
  • At least one power supply (14) which supplies the required energy
  • at least one control unit (15) which is adapted to generate the power signals required for the mission grips, and to collect the parallel data coming from the mission grips and to transmit the said data serially to the mission computer (12).
  • a preferred embodiment of the mission grip system (1) of the present invention includes a pilot mission grip (2), copilot left hand mission grip (3) and/or copilot right hand mission grip (4).
  • Each mission grip has a button guard (6) on the gun, missile and/or laser fire trigger (5), and thus accidental pressing of the fire trigger (5) (preferably the button that corresponds to the index finger) by the pilot/copilot is prevented ( Figure 3, 4 and 5).
  • the said button guard (6) is located at the rear part of the handle on the mission grips such that it is connected to a shaft and can rotate around the axis of the said shaft ( Figure 3, 4).
  • the button guard (6) is positioned such that it covers at least one of the buttons provided on the upper part of the handle and that it rotates around the axis of a shaft ( Figure 5). When the fire trigger (5) is intended to be pressed, the button guard (6) is lifted upwards to access the fire trigger (5).
  • At least one sunk button (7) which is assigned for performance of critical missions and which is arranged as sunk in the body of at least one of the mission grips ( Figure 6).
  • the handle parts of the body are produced in an ergonomic form in order to prevent the hand from slipping on the mission grips and getting tired.
  • illumination panels which are compatible with night vision goggles used in aviation, provided on the front surface of at least one of the mission grips.
  • the labels which are provided on the front part of the mission grips, and which indicate the key functions can be seen more easily in night flights, and the pilots are enabled to use the weapon systems more easily and effectively in night flights.
  • a second protrusion (9) which is provided on the base of at least one of the mission grips and which extends forward or sideward preferably parallel to the ground plane (Figure 7).
  • the said second protrusion (9) contacts the bottom part of the hand and prevents the hand from slipping downwards from the handle and thus prevents the user from losing control of the mission grip.
  • the discrete signals coming from the pilot mission grip (2), copilot left hand mission grip (3) and copilot right hand mission grip (4) are transmitted to the gun interface unit (10), weapon interface unit (11), mission computer (12) and the control units (15).
  • the said gun interface unit (10) generates control signals according to the discrete control and condition signals coming from the mission grips for controlling and firing the gun units in the aircraft and transmits these signals to the gun unit that will be controlled; and generates location information from the data coming from the gun unit location sensors and transmits this information to the gun unit that will be directed.
  • the weapon interface unit (11) generates the power and discrete signals required to fire the laser guided missiles, unguided missiles, air-to-air missiles and antitank missiles which are integrated to the aircraft.
  • the control unit also reads the key information coming from the control levers (collective & cyclic), by which basic flight controls are carried out, generates the power signals required for the mission grips in accordance with the discrete signals coming from the mission grips, and upon collecting numerous parallel data coming from the mission grips, transmits them serially to the mission computer (12).
  • control units there are provided two control units (15), one for the discrete signals coming from the pilot mission grip (2), and the other for the ones coming from the copilot left hand mission grip (3) and copilot right hand mission grip (4) ( Figure 9, 10).
  • the said control units (15) are conjugated and are backup units for each other. In case of failure of any one of them, the other control unit (15) enables the whole system to remain active.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Control Devices (AREA)
  • Manipulator (AREA)

Abstract

The present invention relates to a mission grip system (1) which enables the pilot/copilot to control the critical mission equipment in aircrafts simultaneously, and basically comprises a pilot mission grip (2); a copilot left hand mission grip (3) and/or a copilot right hand mission grip (4); at least one gun interface unit (10), which is adapted to generate control signals according to the discrete control and condition signals coming from the mission grips for controlling and firing the gun units in the aircraft and to transmit these signals to the gun unit that will be controlled; a weapon interface unit (11) which is adapted to generate the power and discrete signals required to fire the missiles integrated to the aircraft; a mission computer (12) which is adapted to control all mission equipment such as moving digital map system, weapon system and target detection/sighting system of the aircraft and to provide the data transmission between the said equipment; at least one control unit (15) which is adapted to generate the power signals required for the mission grips, and to collect the parallel data coming from the mission grips and to transmit the said data serially to the mission computer (12).

Description

DESCRIPTION
MULTI-FUNCTIONAL MISSION GRIP SYSTEM FOR A VEHICLE Field of the Invention
The present invention relates to a mission grip system which enables to control moving digital map system, weapon system and target detection/sighting system equipment by means of a copilot right hand mission grip, copilot left hand mission grip, pilot mission grip and control units integrated into aircrafts (e.g. T-129 Atak (Attack) helicopter).
Background of the Invention In the state of the art applications, the interfaces between the user and the moving digital map system, weapon system and target detection/sighting system can be provided by limited means, and time consuming methods that are difficult to be accessed. The number of the systems controlled by the mission grips used in aircrafts is limited and/or they are more inconvenient. This in turn increases the user' s time loss and error rate.
Again in these applications, non-ergonomic designs made for the users cause the user to get tired and fail performing necessary functions as required, and the system to occupy a more than necessary space in the cockpit in long duration flights. Furthermore, failure to read the labels on the mission grips in night flights brings along possible problems.
Problems Solved by the Invention The objective of the present invention is to provide a mission grip system which enables the user to control different systems simultaneously in aircrafts. Thanks to the present invention, a more convenient accessibility is provided between the pilots and the moving digital map system, weapon system and target detection/sighting system, and by the support of more user interfaces, the pilots are enabled to save time and the error rate is reduced.
Another objective of the present invention is to provide a mission grip system which, in addition to providing ease of use in short and long duration flights of the users by means of its ergonomic design architecture, provides advantage of space for the other equipment in the cockpit owing to the fact that it occupies a smaller space in the cockpit.
By means of the illumination panels provided on the front side of the mission grips, the labels indicating the key functions can be read in night flights and the said mission equipment are enabled to be used more effectively in night conditions compared to the past.
The mission grip system of the present invention is developed in compliance with the environmental requirements determined by military standards (MIL-HDBK- 5400, MIL-STD-810, MIL-STD-704 and MIL-STD-461). Within this framework, altitude, low and high temperature, thermal shock, humidity, vibration, mechanical shock, dust, salty atmosphere, rain, acceleration, solar radiation, temperature-altitude, temperature-vibration, power and EMI/EMC tests are applied to the equipment. Detailed Description of the Invention
A mission grip system developed to fulfill the objective of the present invention is illustrated in the accompanying figures wherein: Figure 1 is the schematic view of the mission grip system.
Figure 2 is a perspective view of the pilot mission grip. Figure 3 is a perspective view of the button guard on the gun/missile fire trigger. Figure 4 is a side view of the button guard on the gun/missile fire trigger.
Figure 5 is a perspective view of the button guard on the laser fire trigger.
Figure 6 is a view of the sunk button in the mission grip.
Figure 7 is a perspective view of the first protrusions and the second protrusion in the mission grip.
Figure 8 is a perspective view of the copilot left hand and right hand mission grips.
Figure 9 is a front perspective view of the control unit.
Figure 10 is a rear perspective view of the control unit.
The components in the figures are given reference numbers as follows:
I. Mission grip system
2. Pilot mission grip
3. Copilot left hand mission grip
4. Copilot right hand mission grip
5. Fire trigger
6. Button guard
7. Sunk button
8. First protrusion
9. Second protrusion
10. Gun interface unit
II. Weapon interface unit
12. Mission computer
13. Control levers (cyclic and collective)
14. Power supply
15. Control unit A mission grip system (1) which enables the pilot/copilot to control the critical mission equipment in aircrafts simultaneously, basically comprises at least one pilot mission grip (2),
at least one copilot left hand mission grip (3) and/or at least one copilot right hand mission grip (4),
at least one fire trigger (5) which enables to fire the gun, missile and/or laser located in the aircraft,
at least one button guard (6) which prevents accidental pressing of the fire trigger (5) by covering the said trigger,
at least one sunk button (7) which is assigned for critical missions and which is sunk in at least one of the mission grips,
at least one first protrusion (8) which is provided on at least one of the mission grips and which prevents slipping of the user's hand from the mission grip by providing a friction between the hand and the handle, at least one second protrusion (9) which is provided at the base of at least one of the mission grips and which contacts the bottom of the hand and extends outwards preferably parallel to the ground plane for preventing the hand from slipping downwards,
at least one gun interface unit (10), which is adapted to generate control signals according to the discrete control and condition signals coming from the mission grips for controlling and firing the gun units in the aircraft and to transmit these signals to the gun unit that will be controlled; and to generate location information from the data coming from the gun unit location sensors and to transmit these information to the gun unit that will be directed,
at least one weapon interface unit (11) which is adapted to generate the power and discrete signals required to fire the laser guided missiles, unguided missiles, air-to-air missiles and/or antitank missiles which are integrated to the aircraft,
at least one mission computer (12) which is adapted to control all mission equipment such as moving digital map system, weapon system and target detection/sighting system of the aircraft and to provide the data transmission between the said equipment, control levers (collective & cyclic) (13) which enable to perform the basic flight controls,
at least one power supply (14) which supplies the required energy, at least one control unit (15) which is adapted to generate the power signals required for the mission grips, and to collect the parallel data coming from the mission grips and to transmit the said data serially to the mission computer (12).
A preferred embodiment of the mission grip system (1) of the present invention includes a pilot mission grip (2), copilot left hand mission grip (3) and/or copilot right hand mission grip (4). Each mission grip has a button guard (6) on the gun, missile and/or laser fire trigger (5), and thus accidental pressing of the fire trigger (5) (preferably the button that corresponds to the index finger) by the pilot/copilot is prevented (Figure 3, 4 and 5).
In one embodiment of the invention, the said button guard (6) is located at the rear part of the handle on the mission grips such that it is connected to a shaft and can rotate around the axis of the said shaft (Figure 3, 4). In another embodiment of the invention, the button guard (6) is positioned such that it covers at least one of the buttons provided on the upper part of the handle and that it rotates around the axis of a shaft (Figure 5). When the fire trigger (5) is intended to be pressed, the button guard (6) is lifted upwards to access the fire trigger (5).
In one embodiment of the invention, there is provided at least one sunk button (7) which is assigned for performance of critical missions and which is arranged as sunk in the body of at least one of the mission grips (Figure 6).
In one embodiment of the invention, the handle parts of the body are produced in an ergonomic form in order to prevent the hand from slipping on the mission grips and getting tired. As can be seen in Figure 7, there is a plurality of first protrusions (8) on the said handle. These first protrusions (8) enable a friction between the hand and the handle, and this way the user's hand is prevented from slipping from the mission grip.
In one embodiment of the invention, there are illumination panels, which are compatible with night vision goggles used in aviation, provided on the front surface of at least one of the mission grips. Thus, the labels, which are provided on the front part of the mission grips, and which indicate the key functions can be seen more easily in night flights, and the pilots are enabled to use the weapon systems more easily and effectively in night flights.
In one embodiment of the invention, there is a second protrusion (9) which is provided on the base of at least one of the mission grips and which extends forward or sideward preferably parallel to the ground plane (Figure 7). The said second protrusion (9) contacts the bottom part of the hand and prevents the hand from slipping downwards from the handle and thus prevents the user from losing control of the mission grip.
In a preferred embodiment of the invention, the discrete signals coming from the pilot mission grip (2), copilot left hand mission grip (3) and copilot right hand mission grip (4) are transmitted to the gun interface unit (10), weapon interface unit (11), mission computer (12) and the control units (15). The said gun interface unit (10), generates control signals according to the discrete control and condition signals coming from the mission grips for controlling and firing the gun units in the aircraft and transmits these signals to the gun unit that will be controlled; and generates location information from the data coming from the gun unit location sensors and transmits this information to the gun unit that will be directed. The weapon interface unit (11) generates the power and discrete signals required to fire the laser guided missiles, unguided missiles, air-to-air missiles and antitank missiles which are integrated to the aircraft. Furthermore, it conveys the condition and status information of the discrete and power signals digitally via a defined data bus to the mission computer (12). The control unit (15) also reads the key information coming from the control levers (collective & cyclic), by which basic flight controls are carried out, generates the power signals required for the mission grips in accordance with the discrete signals coming from the mission grips, and upon collecting numerous parallel data coming from the mission grips, transmits them serially to the mission computer (12).
In a preferred embodiment of the invention, there are provided two control units (15), one for the discrete signals coming from the pilot mission grip (2), and the other for the ones coming from the copilot left hand mission grip (3) and copilot right hand mission grip (4) (Figure 9, 10). The said control units (15) are conjugated and are backup units for each other. In case of failure of any one of them, the other control unit (15) enables the whole system to remain active.

Claims

A mission grip system (1) which enables the pilot/copilot to control the critical mission equipment in aircrafts simultaneously, basically comprising
at least one pilot mission grip (2),
at least one copilot left hand mission grip (3) and/or at least one copilot right hand mission grip (4),
and characterized by
at least one gun interface unit (10), which is adapted to generate control signals according to the discrete control and condition signals coming from the mission grips for controlling and firing the gun units in the aircraft and to transmit these signals to the gun unit that will be controlled; and to generate location information from the data coming from the gun unit location sensors and to transmit these information to the gun unit that will be directed,
at least one weapon interface unit (11) which is adapted to generate the power and discrete signals required to fire the laser guided missiles, unguided missiles, air-to-air missiles and/or antitank missiles which are integrated to the aircraft,
at least one mission computer (12) which is adapted to control all mission equipment such as moving digital map system, weapon system and target detection/sighting system of the aircraft and to provide the data transmission between the said equipment,
at least one power supply (14) which supplies the required energy, at least one control unit (15) which is adapted to generate the power signals required for the mission grips, and to collect the parallel data coming from the mission grips and to transmit the said data serially to the mission computer (12).
2. A mission grip system (1) according to Claim 1, characterized by at least one button guard (6) which prevents accidental pressing of the fire trigger (5) by covering the said trigger.
3. A mission grip system (1) according to Claim 2, characterized by the button guard (6), which is located at the rear part of the handle on the mission grips such that it is connected to a shaft and can rotate around the axis of the said shaft.
4. A mission grip system (1) according to Claim 1, characterized by at least one sunk button (7) which is assigned for critical missions and which is sunk in at least one of the mission grips.
5. A mission grip system (1) according to Claim 1, characterized by at least one first protrusion (8) which is provided on at least one of the mission grips and which prevents slipping of the user's hand from the mission grip by providing a friction between the hand and the handle.
6. A mission grip system (1) according to Claim 1, characterized by at least one second protrusion (9) which is provided at the base of at least one of the mission grips and which contacts the bottom of the hand and extends outwards preferably parallel to the ground plane for preventing the hand from slipping downwards.
7. A mission grip system (1) according to Claim 1, characterized by two control units (15); one of which is for the discrete signals coming from the pilot mission grip (2), and the other for the ones coming from the copilot left hand mission grip (3) and copilot right hand mission grip (4); and which are conjugates of each other.
8. A mission grip system (1) according to Claim 1, characterized by illumination panels, which are located on the front side of the mission grips and are provided on the front part of at least one of the mission grips, and which illuminate the labels indicating the key functions in night flights.
PCT/IB2015/054954 2015-07-01 2015-07-01 Multi-functional mission grip system for a vehicle WO2017001898A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
PL421909A PL421909A1 (en) 2015-07-01 2015-07-01 Multi-function joystick system for a vehicle
TN2017000151A TN2017000151A1 (en) 2015-07-01 2015-07-01 Multi-functional mission grip system for a vehicle
ZA2017/02383A ZA201702383B (en) 2015-07-01 2017-04-04 Multi-functional mission grip system for a vehicle

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR2015/08118 2015-07-01
TR201508118 2015-07-01

Publications (1)

Publication Number Publication Date
WO2017001898A1 true WO2017001898A1 (en) 2017-01-05

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ID=54011051

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2015/054954 WO2017001898A1 (en) 2015-07-01 2015-07-01 Multi-functional mission grip system for a vehicle

Country Status (4)

Country Link
PL (1) PL421909A1 (en)
TN (1) TN2017000151A1 (en)
WO (1) WO2017001898A1 (en)
ZA (1) ZA201702383B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11001141B2 (en) 2019-08-05 2021-05-11 Ford Global Technologies, Llc Joystick for vehicle

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3198922A (en) * 1961-05-25 1965-08-03 Applic Mach Motrices Handle for pilot's lever
US6264146B1 (en) * 1999-12-07 2001-07-24 The Boeing Company Portable controller for an aircraft
US20070262206A1 (en) * 2006-05-12 2007-11-15 Sikorsky Aircraft Corporation Multi-functional mission grip for a vehicle
US20120313853A1 (en) * 2010-09-29 2012-12-13 United States Government, As Represented By The Secretary Of The Navy Hand -interface for weapon station
KR20140086942A (en) * 2014-06-12 2014-07-08 주식회사 성진테크윈 Control stick structure

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3198922A (en) * 1961-05-25 1965-08-03 Applic Mach Motrices Handle for pilot's lever
US6264146B1 (en) * 1999-12-07 2001-07-24 The Boeing Company Portable controller for an aircraft
US20070262206A1 (en) * 2006-05-12 2007-11-15 Sikorsky Aircraft Corporation Multi-functional mission grip for a vehicle
US20120313853A1 (en) * 2010-09-29 2012-12-13 United States Government, As Represented By The Secretary Of The Navy Hand -interface for weapon station
KR20140086942A (en) * 2014-06-12 2014-07-08 주식회사 성진테크윈 Control stick structure

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11001141B2 (en) 2019-08-05 2021-05-11 Ford Global Technologies, Llc Joystick for vehicle

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Publication number Publication date
TN2017000151A1 (en) 2018-10-19
ZA201702383B (en) 2018-08-29
PL421909A1 (en) 2018-02-26

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