US20140332627A1 - Control and safety system for an airplane - Google Patents
Control and safety system for an airplane Download PDFInfo
- Publication number
- US20140332627A1 US20140332627A1 US14/327,516 US201414327516A US2014332627A1 US 20140332627 A1 US20140332627 A1 US 20140332627A1 US 201414327516 A US201414327516 A US 201414327516A US 2014332627 A1 US2014332627 A1 US 2014332627A1
- Authority
- US
- United States
- Prior art keywords
- exhaust
- control system
- airplane
- parachute
- landing pad
- Prior art date
- Legal status (The legal status 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 status listed.)
- Abandoned
Links
- 239000000463 material Substances 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims 2
- 230000001360 synchronised effect Effects 0.000 claims 1
- 239000002184 metal Substances 0.000 description 2
- 230000003213 activating effect Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/14—Attitude, flight direction, or altitude control by jet reaction the jets being other than main propulsion jets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/54—Floats
- B64C25/56—Floats inflatable
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
Definitions
- This invention relates to features on an airplane that assist in safety and control.
- the present invention is directed to a control and safety system that increases the maneuverability and safety of airplanes.
- the system comprises adjustable jet engine exhaust directions, a series of parachutes, and landing pads for an airplane.
- the object of this invention is to give an aircraft increased maneuverability, while giving an aircraft a way to land safely in the case of an emergency.
- the increased maneuverability can assist a plane in avoiding accidents, in fighting other planes, or for more control in take-off and landing.
- the parachutes and landing pads can save a plane and the people inside it from destruction even if the engines fail.
- FIG. 1 shows an airplane with the control and safety systems deployed
- FIG. 2 shows a power jet controller with a rotating jet engine providing forward thrust
- FIG. 3 shows a power jet controller with a rotating jet engine providing upward thrust
- FIG. 4 shows a power jet controller with an exhaust reservoir with the back hole open
- FIG. 5 shows a power jet controller with an exhaust reservoir with the bottom hole open
- FIG. 6 shows a deployed main parachute and a deflated backup parachute
- FIG. 7 shows a failed main parachute and an inflated backup parachute
- FIG. 8 shows a landing pad in its deflated state
- FIG. 9 shows a landing pad in its inflated state.
- control and safety system 100 comprising a power jet controller 120 , a plurality of parachutes 130 , and inflatable landing pads 140 can be used to increase the control and safety of an airplane 110 .
- a power jet controller is a new device that will allow a jet airplane to maneuver quickly in different directions that other airplanes cannot.
- the embodiments noted here are the switch-engine type power jet controller 120 and the ball-type power jet controller 400 .
- the switch-engine type power jet controller 120 is a device that rotates a mounted jet engine 200 of an airplane with up to a full 360° of motion.
- FIG. 2 shows the intake 202 taking air into the engine 200 and expelling the air out at the exhaust 204 towards the right, causing a thrust to the left.
- FIG. 3 shows the engine rotated so the air is expelled downwards, causing thrust upwards.
- the angle of orientation would be controlled by the pilot in a cockpit using a control panel. Once the desired angle is reached, the jet engine orientation would be locked in.
- the jet engine is attached to a rotatable metal ring 210 with retractable pins 212 .
- the pins 212 can extend into holes 214 of a fixed metal ring 220 on the airplane 110 to lock the jet engine 200 in place as shown in FIG. 3 .
- a pilot in a cockpit could control the power jet controller 120 with a control pad.
- the jet engine 200 may use a hydraulic pump or an electric pump with motors and hydraulic arms for rotation. When mounted on the side of an airplane, this would allow a plane to fly up, down, backwards and forwards. This would assist in landing, takeoff, and maneuvering in the air. This would also help avoid accidents or give a combat jet fighter an advantage.
- the size and range of motion of the power jet controller 120 would depend on the size of the plane 110 and engine 200 . Other methods of rotating the engine 200 may also be implemented.
- the ball-type power jet controller 400 connects an exhaust reservoir to the exhaust 204 of the engine 200 of a jet airplane 110 .
- the exhaust reservoir is ball-shaped and has holes that can be covered 410 or uncovered 420 .
- a control panel in the cockpit can be utilized by a pilot to control which of those holes are open at any given time.
- the control panel could be analog control switches that activate a motor to move coverings of the exhaust reservoir by use of mechanical arms.
- the jet exhaust stream will exit the exhaust reservoir from whichever hole is open. This will provide thrust to the airplane in the opposite direction.
- a cockpit chose to keep the top hole open
- the jet engine exhaust would exit the exhaust reservoir from the top, giving the airplane thrust downwards.
- the cockpit altered the coverings to make the hole on the left open, the airplane would have thrust to the right. This gives the pilot increased control over the airplane to avoid accidents in the air. In a combat jet fighter, this would give an important advantage of maneuverability to the plane.
- the device would be placed directly behind and four feet above a cockpit. A reflector between the cockpit and the power jet controller would protect the pilot from heat. The device would be connected to the jet engine 200 by the use of exhaust lines.
- the plurality of parachutes 130 for the safety system would further increase the safety of the airplane 110 .
- this system could save the passengers, crew, and airplane 110 .
- a pilot would be able to activate the plurality of parachutes 130 from the cockpit by way of an analog control device. This would remove coverings 612 to provide an opening 610 in different sections of the airplane by use of an electric or hydraulic motor.
- a primary parachute 630 with an attachment point 632 on a parachute attachment line 620 would then be released out of the opening 610 as in FIG. 6 .
- a reserve parachute 640 with a reserve attachment point 642 on the parachute attachment line 620 could slide into place and activate as in FIG. 7 .
- the number, size, and shape of the parachutes will depend on the kind of airplane 110 .
- the inflatable landing pad 800 can be activated in an emergency situation.
- the landing pad 800 will be made of a strong, flexible material like rubber to cushion the bottom of a plane for a softer and safer landing.
- a pilot activating an analog control system will cause a sliding door 812 on the bottom of the airplane to move, providing an opening 810 while also opening a pressure valve 840 of gas 820 that has a connection 830 to the landing pad 800 and inflates the landing pad 800 .
- the sliding door 812 can be controlled by use of an electric and/or hydraulic engine.
- the control and safety system 100 can include a plurality of landing pads 140 .
- an aircraft can have five landing pads for five different areas of the plane.
- An example of a gas 820 that can be used to inflate the landing pad 800 is CO2.
- the number, size, and shape of the lands pads 140 will depend on the kind of airplane 110 .
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
- Emergency Lowering Means (AREA)
Abstract
A Safety and Control System for an airplane that allows a pilot to adjust the direction of an airplane and protect the plane in emergency situations. The engine of the plane can create thrust in more than one direction for improved maneuverability. A plurality of parachutes and landing pads can be deployed to protect the plane, along with the people in it.
Description
- This patent application is a continuation of U.S. patent application Ser. No. 11/582,046, entitled “Control and Safety System for an Airplane,” filed May 8, 2007, which is incorporated in its entirety here by this reference.
- This invention relates to features on an airplane that assist in safety and control.
- Current airplanes use jets that only provide thrust in one direction. An increase in the number of directions of thrust could allow jets to increase maneuverability in the air. In addition, aircrafts lack sufficient safety systems for dealing with engine failures. For the foregoing reasons there is a need for increased maneuverability and safety in airplanes.
- The present invention is directed to a control and safety system that increases the maneuverability and safety of airplanes. As shown in
FIG. 1 , the system comprises adjustable jet engine exhaust directions, a series of parachutes, and landing pads for an airplane. - The object of this invention is to give an aircraft increased maneuverability, while giving an aircraft a way to land safely in the case of an emergency. The increased maneuverability can assist a plane in avoiding accidents, in fighting other planes, or for more control in take-off and landing. The parachutes and landing pads can save a plane and the people inside it from destruction even if the engines fail.
-
FIG. 1 shows an airplane with the control and safety systems deployed; -
FIG. 2 shows a power jet controller with a rotating jet engine providing forward thrust; -
FIG. 3 shows a power jet controller with a rotating jet engine providing upward thrust; -
FIG. 4 shows a power jet controller with an exhaust reservoir with the back hole open; -
FIG. 5 shows a power jet controller with an exhaust reservoir with the bottom hole open; -
FIG. 6 shows a deployed main parachute and a deflated backup parachute; -
FIG. 7 shows a failed main parachute and an inflated backup parachute; -
FIG. 8 shows a landing pad in its deflated state; and -
FIG. 9 shows a landing pad in its inflated state. - As shown in
FIG. 1 , the control andsafety system 100 comprising apower jet controller 120, a plurality ofparachutes 130, andinflatable landing pads 140 can be used to increase the control and safety of anairplane 110. - A power jet controller is a new device that will allow a jet airplane to maneuver quickly in different directions that other airplanes cannot. The embodiments noted here are the switch-engine type
power jet controller 120 and the ball-typepower jet controller 400. - As shown in
FIGS. 2 and 3 , the switch-engine typepower jet controller 120 is a device that rotates a mountedjet engine 200 of an airplane with up to a full 360° of motion.FIG. 2 shows theintake 202 taking air into theengine 200 and expelling the air out at theexhaust 204 towards the right, causing a thrust to the left.FIG. 3 shows the engine rotated so the air is expelled downwards, causing thrust upwards. The angle of orientation would be controlled by the pilot in a cockpit using a control panel. Once the desired angle is reached, the jet engine orientation would be locked in. In one embodiment, the jet engine is attached to arotatable metal ring 210 withretractable pins 212. Thepins 212 can extend intoholes 214 of afixed metal ring 220 on theairplane 110 to lock thejet engine 200 in place as shown inFIG. 3 . A pilot in a cockpit could control thepower jet controller 120 with a control pad. In some embodiments, thejet engine 200 may use a hydraulic pump or an electric pump with motors and hydraulic arms for rotation. When mounted on the side of an airplane, this would allow a plane to fly up, down, backwards and forwards. This would assist in landing, takeoff, and maneuvering in the air. This would also help avoid accidents or give a combat jet fighter an advantage. The size and range of motion of thepower jet controller 120 would depend on the size of theplane 110 andengine 200. Other methods of rotating theengine 200 may also be implemented. - As shown in
FIGS. 4 and 5 , the ball-typepower jet controller 400 connects an exhaust reservoir to theexhaust 204 of theengine 200 of ajet airplane 110. The exhaust reservoir is ball-shaped and has holes that can be covered 410 or uncovered 420. Although this embodiment uses a ball shape, other shapes are also viable. A control panel in the cockpit can be utilized by a pilot to control which of those holes are open at any given time. In one embodiment, the control panel could be analog control switches that activate a motor to move coverings of the exhaust reservoir by use of mechanical arms. - The jet exhaust stream will exit the exhaust reservoir from whichever hole is open. This will provide thrust to the airplane in the opposite direction. For example, in a ball-type power jet controller with six holes corresponding to the top, bottom, front, back, left, and right, if a cockpit chose to keep the top hole open, the jet engine exhaust would exit the exhaust reservoir from the top, giving the airplane thrust downwards. If the cockpit altered the coverings to make the hole on the left open, the airplane would have thrust to the right. This gives the pilot increased control over the airplane to avoid accidents in the air. In a combat jet fighter, this would give an important advantage of maneuverability to the plane. In one embodiment, the device would be placed directly behind and four feet above a cockpit. A reflector between the cockpit and the power jet controller would protect the pilot from heat. The device would be connected to the
jet engine 200 by the use of exhaust lines. - As shown in
FIGS. 1 , 6, and 7, the plurality ofparachutes 130 for the safety system would further increase the safety of theairplane 110. In case of engine failure, this system could save the passengers, crew, andairplane 110. A pilot would be able to activate the plurality ofparachutes 130 from the cockpit by way of an analog control device. This would removecoverings 612 to provide anopening 610 in different sections of the airplane by use of an electric or hydraulic motor. Aprimary parachute 630 with anattachment point 632 on aparachute attachment line 620 would then be released out of theopening 610 as inFIG. 6 . In case of failure of aprimary parachute 630, areserve parachute 640 with areserve attachment point 642 on theparachute attachment line 620 could slide into place and activate as inFIG. 7 . The number, size, and shape of the parachutes will depend on the kind ofairplane 110. - As shown in
FIGS. 8 and 9 , theinflatable landing pad 800 can be activated in an emergency situation. Thelanding pad 800 will be made of a strong, flexible material like rubber to cushion the bottom of a plane for a softer and safer landing. A pilot activating an analog control system will cause a slidingdoor 812 on the bottom of the airplane to move, providing anopening 810 while also opening apressure valve 840 ofgas 820 that has aconnection 830 to thelanding pad 800 and inflates thelanding pad 800. The slidingdoor 812 can be controlled by use of an electric and/or hydraulic engine. The control andsafety system 100 can include a plurality oflanding pads 140. For example, an aircraft can have five landing pads for five different areas of the plane. An example of agas 820 that can be used to inflate thelanding pad 800 is CO2. The number, size, and shape of thelands pads 140 will depend on the kind ofairplane 110.
Claims (20)
1. A control system for an airplane comprising an exhaust device to control a direction of jet engine exhaust, wherein the exhaust device comprises:
an intake;
an exhaust reservoir attached to the intake, wherein the exhaust reservoir comprises exhaust openings and exhaust covers;
wherein an exhaust opening in a closed configuration is sealed by an exhaust cover, wherein an exhaust opening in an open configuration is not sealed by the exhaust cover;
wherein the intake is configured to receive the jet engine exhaust and transfer the jet engine exhaust to the exhaust reservoir; and
wherein the exhaust reservoir is configured to receive the jet engine exhaust from the intake and release the jet engine exhaust through at least one exhaust opening in an open configuration to provide thrust to the airplane.
2. The control system of claim 1 , wherein the exhaust reservoir comprises six exhaust openings, wherein the exhaust openings are located at a front position, a back position, a left position, a right position, a top position, and a bottom position.
3. The control system of claim 2 , wherein the exhaust reservoir is spherical.
4. The control system of claim 3 , wherein the exhaust device has a stationary state and a transition state, wherein the stationary state has five exhaust openings in the closed configuration and one exhaust opening in the open configuration to provide thrust in the direction of the exhaust opening in the open configuration, wherein the transition state has four exhaust openings in the closed configuration and at least one exhaust opening in the open configuration.
5. The control system of claim 4 , further comprising controls in a cockpit to control the exhaust device.
6. The control system of claim 5 , wherein the intake is attached to the exhaust reservoir between the exhaust openings at the front position and bottom position.
7. The control system of claim 6 , wherein the intake is secured to a jet engine.
8. The control system of claim 7 , wherein the exhaust device is made of a material that can handle a pressure and a heat of the jet engine exhaust.
9. The control system of claim 8 , further comprising a second exhaust device.
10. The control system of claim 9 , wherein exhaust devices have synchronized controls to provide thrust in a same direction.
11. A control system comprising a safety system for the airplane, wherein the safety system comprises:
a plurality of parachutes, wherein at least one parachute opens in case of an emergency; and
controls in a cockpit to activate the at least one parachute.
12. The control system of claim 11 , wherein the controls further activate at least one sliding door to provide an opening for the at least one parachute.
13. The control system of claim 12 , further comprising at least one backup parachute that deploys if the at least one parachute fails.
14. The control system of claim 13 , wherein the plurality of parachutes comprises a first parachute and a second parachute, wherein the first parachute differs in size and shape from the second parachute.
15. The control system of claim 14 , wherein the first parachute opens on top of a front portion of the airplane and the second parachute opens on top of a rear portion of the airplane.
16. A control system comprising a safety system for the airplane, wherein the safety system comprises:
at least one inflatable landing pad for the airplane;
wherein the landing pad is stored deflated inside the airplane; and
wherein the landing pad is activated to inflate the landing pad and cover at least a
portion of a bottom of the airplane to cushion the airplane.
17. The control system of claim 16 , further comprising controls in a cockpit to activate the at least one landing pad.
18. The control system of claim 17 , wherein the landing pad comprises strong, flexible material.
19. The control system of claim 18 , wherein the controls control at least one valve to release pressured gas to the landing pad.
20. The control system of claim 19 , wherein the at least one inflatable landing pad comprises a front landing pad and a rear landing pad, wherein the front landing pad is released from a bottom of a front portion of the airplane and the rear landing pad is released from a bottom of a rear portion of the airplane.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/327,516 US20140332627A1 (en) | 2007-05-08 | 2014-07-09 | Control and safety system for an airplane |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/582,046 US8794567B2 (en) | 2007-05-08 | 2007-05-08 | Control and safety system for an airplane |
US14/327,516 US20140332627A1 (en) | 2007-05-08 | 2014-07-09 | Control and safety system for an airplane |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/582,046 Continuation US8794567B2 (en) | 2007-05-08 | 2007-05-08 | Control and safety system for an airplane |
Publications (1)
Publication Number | Publication Date |
---|---|
US20140332627A1 true US20140332627A1 (en) | 2014-11-13 |
Family
ID=42195333
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/582,046 Active 2030-08-10 US8794567B2 (en) | 2007-05-08 | 2007-05-08 | Control and safety system for an airplane |
US14/327,516 Abandoned US20140332627A1 (en) | 2007-05-08 | 2014-07-09 | Control and safety system for an airplane |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/582,046 Active 2030-08-10 US8794567B2 (en) | 2007-05-08 | 2007-05-08 | Control and safety system for an airplane |
Country Status (1)
Country | Link |
---|---|
US (2) | US8794567B2 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20180155038A1 (en) * | 2016-12-02 | 2018-06-07 | Joseph Miller | Aircraft Parachute System |
US10118707B2 (en) | 2016-02-12 | 2018-11-06 | Cirrus Design Corporation | Aircraft parachute deployment autopilot |
USRE49214E1 (en) | 2009-01-13 | 2022-09-20 | Cirrus Design Corporation | Intelligent ballistic parachute system that performs pre-activation and/or post-activation actions |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102167162A (en) * | 2011-03-10 | 2011-08-31 | 洪瑞庆 | Ultra-high pressure fluid jetting power track transferring system and method for aircraft |
CN202491924U (en) * | 2012-02-17 | 2012-10-17 | 孙磊 | Airplane anti-falling and self-rescuing device |
US8777154B2 (en) * | 2012-07-09 | 2014-07-15 | United Technologies Corporation | Apparatus and method for preventing gas turbine engine freezing |
US9613539B1 (en) * | 2014-08-19 | 2017-04-04 | Amazon Technologies, Inc. | Damage avoidance system for unmanned aerial vehicle |
CN108216585A (en) * | 2018-01-29 | 2018-06-29 | 成都市煜沣科技有限公司 | A kind of jet-propelled undercarriage of civil small-scale unmanned plane |
US11780595B1 (en) * | 2022-11-15 | 2023-10-10 | A-Hamid Hakki | System, method, and apparatus for controlled descent |
Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3164337A (en) * | 1959-09-29 | 1965-01-05 | Hawker Aircraft Ltd | Jet aircraft with orientable nozzles for vertical or forward movement |
US3528247A (en) * | 1967-03-17 | 1970-09-15 | Motoren Turbinen Union | Exhaust system for vtol aircraft |
US4140290A (en) * | 1972-07-07 | 1979-02-20 | Vereinigte Flugtechnische Werke-Fokker Gmbh | V/STOL aircraft with thrust control |
US5816042A (en) * | 1996-12-27 | 1998-10-06 | United Technologies Corporation | Flow diverter system for multiple streams for gas turbine engines |
US6371407B1 (en) * | 2000-07-05 | 2002-04-16 | Lockheed Martin Corporation | Mechanism for vectoring exhaust flow |
US20070018034A1 (en) * | 2005-07-12 | 2007-01-25 | Dickau John E | Thrust vectoring |
US20100301158A1 (en) * | 2009-05-29 | 2010-12-02 | Rolls-Royce Plc | Aircraft having a lift/propulsion unit |
US20110315827A1 (en) * | 2009-03-12 | 2011-12-29 | Bob Collins | Wing Extension Control Surface |
US8205821B2 (en) * | 2006-12-13 | 2012-06-26 | General Electric Company | Engine propulsion system and methods of assembling the same |
US8215589B2 (en) * | 2004-01-23 | 2012-07-10 | Janeke Charl E | Reversible space plane |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3068647A (en) * | 1960-03-23 | 1962-12-18 | Ling Temco Vought Inc | Propulsion and control system for multi-engine turbine powered aircraft |
US3107887A (en) * | 1962-04-12 | 1963-10-22 | Jackie N Dixon | Aircraft safety system |
US3318095A (en) * | 1964-05-14 | 1967-05-09 | Bristol Siddeley Engines Ltd | Jet propulsion plant for aircraft with gas turbine engine and with fan driven by exhaust of such engine |
US3298637A (en) * | 1964-06-15 | 1967-01-17 | Lee Shao-Tang | Engine inlet protective screen arrangement |
US3289980A (en) * | 1964-12-07 | 1966-12-06 | Lockheed Aircraft Corp | Thrust system for vtol aircraft |
US3833192A (en) * | 1972-11-13 | 1974-09-03 | G Spector | Safety device for airplanes land safety |
US4298177A (en) * | 1979-11-09 | 1981-11-03 | Berlongieri John J | Aircraft safety apparatus |
US4699336A (en) * | 1986-05-08 | 1987-10-13 | Peter Diamond | Airplane safety body passenger compartment |
US5297388A (en) * | 1992-04-13 | 1994-03-29 | Rolls-Royce Inc. | Fluid flow duct with alternative outlets |
GB2313580B (en) * | 1996-05-31 | 2000-02-23 | Astovl Limited | An aircraft power plant |
US5899414A (en) * | 1997-07-25 | 1999-05-04 | Duffoo; Jose G. | Aircraft crash prevention system |
US6918244B2 (en) * | 2001-08-17 | 2005-07-19 | John Eugene Dickau | Vertical takeoff and landing aircraft propulsion systems |
US20030127565A1 (en) * | 2002-01-07 | 2003-07-10 | Bernard Haffen | Operation continue life pressurized parachutes |
US7523891B2 (en) * | 2005-12-21 | 2009-04-28 | A-Hamid Hakki | Safety pre-impact deceleration system for vehicles |
KR101125870B1 (en) * | 2011-07-29 | 2012-03-28 | 한국항공우주연구원 | The tiltrotor aircraft |
-
2007
- 2007-05-08 US US11/582,046 patent/US8794567B2/en active Active
-
2014
- 2014-07-09 US US14/327,516 patent/US20140332627A1/en not_active Abandoned
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3164337A (en) * | 1959-09-29 | 1965-01-05 | Hawker Aircraft Ltd | Jet aircraft with orientable nozzles for vertical or forward movement |
US3528247A (en) * | 1967-03-17 | 1970-09-15 | Motoren Turbinen Union | Exhaust system for vtol aircraft |
US4140290A (en) * | 1972-07-07 | 1979-02-20 | Vereinigte Flugtechnische Werke-Fokker Gmbh | V/STOL aircraft with thrust control |
US5816042A (en) * | 1996-12-27 | 1998-10-06 | United Technologies Corporation | Flow diverter system for multiple streams for gas turbine engines |
US6371407B1 (en) * | 2000-07-05 | 2002-04-16 | Lockheed Martin Corporation | Mechanism for vectoring exhaust flow |
US8215589B2 (en) * | 2004-01-23 | 2012-07-10 | Janeke Charl E | Reversible space plane |
US20070018034A1 (en) * | 2005-07-12 | 2007-01-25 | Dickau John E | Thrust vectoring |
US8205821B2 (en) * | 2006-12-13 | 2012-06-26 | General Electric Company | Engine propulsion system and methods of assembling the same |
US20110315827A1 (en) * | 2009-03-12 | 2011-12-29 | Bob Collins | Wing Extension Control Surface |
US20100301158A1 (en) * | 2009-05-29 | 2010-12-02 | Rolls-Royce Plc | Aircraft having a lift/propulsion unit |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
USRE49214E1 (en) | 2009-01-13 | 2022-09-20 | Cirrus Design Corporation | Intelligent ballistic parachute system that performs pre-activation and/or post-activation actions |
US10118707B2 (en) | 2016-02-12 | 2018-11-06 | Cirrus Design Corporation | Aircraft parachute deployment autopilot |
US10399686B2 (en) * | 2016-02-12 | 2019-09-03 | Cirrus Design Corporation | Mechanical timing connection for sequencing airbag activation with rocket for deploying aircraft parachute |
US10414506B2 (en) * | 2016-02-12 | 2019-09-17 | Cirrus Design Corporation | Aircraft parachute system utilizing airbag to assist with parachute deployment |
US10717538B2 (en) | 2016-02-12 | 2020-07-21 | Cirrus Design Corporation | Bridle for aircraft parachute deployment rocket |
US20180155038A1 (en) * | 2016-12-02 | 2018-06-07 | Joseph Miller | Aircraft Parachute System |
Also Published As
Publication number | Publication date |
---|---|
US8794567B2 (en) | 2014-08-05 |
US20100127115A1 (en) | 2010-05-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20140332627A1 (en) | Control and safety system for an airplane | |
US6698685B2 (en) | Circular vertical take off and landing aircraft | |
US5297761A (en) | Multi-axis g-compensating escape cockpit capsule | |
US9027879B1 (en) | Modular adaptive configured helicopter | |
RU2617014C1 (en) | Aircraft | |
US20090212160A1 (en) | Method for producing lateral ejection apparattii for helicopter or plane | |
US20030098388A1 (en) | Circular vertical take off & landing aircraft | |
US7644739B1 (en) | Pressurized actuation system for inflatable structures | |
US3227399A (en) | Safety aircraft system | |
EP3589543B1 (en) | Aircraft provided with a secondary flight assembly | |
US7104499B1 (en) | Rechargeable compressed air system and method for supplemental aircraft thrust | |
US20070102569A1 (en) | Vertical take-off aircraft - P | |
CN107776879A (en) | Aircraft with urgent floating system | |
US9284029B2 (en) | Helicopter external life raft pod | |
US3372893A (en) | Air to ground descent means | |
US4826247A (en) | System for assisting a fighter pilot in checking the six-o'clock position | |
US20130200218A1 (en) | Rotorcraft escape system | |
US8794484B2 (en) | Actuators principally for inflatable systems | |
US3101918A (en) | Emergency ram air cabin pressurization system | |
CN104670502A (en) | Helicopter in-flight shutdown safe-combination soft landing equipment and soft landing method | |
CN105523187A (en) | Low altitude parachute | |
RU2765197C1 (en) | Aircraft rescue system | |
JP2908824B2 (en) | Emergency injection flight seat | |
US3362665A (en) | Air to ground descent means | |
US3833191A (en) | Powered aircraft ejection seat |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |