JPS641698A - Air floating device - Google Patents

Air floating device

Info

Publication number
JPS641698A
JPS641698A JP2097087A JP2097087A JPS641698A JP S641698 A JPS641698 A JP S641698A JP 2097087 A JP2097087 A JP 2097087A JP 2097087 A JP2097087 A JP 2097087A JP S641698 A JPS641698 A JP S641698A
Authority
JP
Japan
Prior art keywords
airframe
center
gravity
duct
distance
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.)
Pending
Application number
JP2097087A
Other languages
Japanese (ja)
Other versions
JPH011698A (en
Inventor
Shigenori Ando
Shuzo Moroto
Nobuaki Miki
Takahiro Iwami
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Aisin AW Co Ltd
Original Assignee
Aisin AW Co Ltd
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 Aisin AW Co Ltd filed Critical Aisin AW Co Ltd
Priority to JP2097087A priority Critical patent/JPS641698A/en
Publication of JPH011698A publication Critical patent/JPH011698A/en
Publication of JPS641698A publication Critical patent/JPS641698A/en
Pending legal-status Critical Current

Links

Abstract

PURPOSE: To secure self stability even if affected by external factors and to dispense with attitude control by setting the ratio of a duct diameter to the distance between the center of gravity and the aerodynamic center of an airframe in a region where it is stabilized against inclination of the airframe and movement in the propelling direction.
CONSTITUTION: An equation of motion is established against inclination of an airframe and movement in the propelling direction, and a coefficient of the specific equation is converted to a function of the ratio of the diameter of a duct 4 against the distance between the airframe center of gravity CG and the aerodynamic center AC, and then, stability conditions of the airframe are acquired. Then, there exists a region where the airframe is stabilized within the range limited by the positive ratio of the diameter of the duct 4 against the distance between the airframe center of gravity CG and the aerodynamic center AC. By adopting the ratio of the diameter of the duct 4 against the distance between the stabilized airframe center of gravity CG and the aerodynamic center AC as a design condition, self stability can be secured even if affected by external factors and a special attitude control is dispensed with.
COPYRIGHT: (C)1989,JPO
JP2097087A 1986-07-18 1987-01-31 Air floating device Pending JPS641698A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2097087A JPS641698A (en) 1986-07-18 1987-01-31 Air floating device

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP61-169395 1986-07-18
JP16939586 1986-07-18
JP2097087A JPS641698A (en) 1986-07-18 1987-01-31 Air floating device

Publications (2)

Publication Number Publication Date
JPH011698A JPH011698A (en) 1989-01-06
JPS641698A true JPS641698A (en) 1989-01-06

Family

ID=26357975

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2097087A Pending JPS641698A (en) 1986-07-18 1987-01-31 Air floating device

Country Status (1)

Country Link
JP (1) JPS641698A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06293296A (en) * 1992-12-28 1994-10-21 Hughes Missile Syst Co Pilotless aircraft for effecting vertical take off and landing and level cruise flight

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06293296A (en) * 1992-12-28 1994-10-21 Hughes Missile Syst Co Pilotless aircraft for effecting vertical take off and landing and level cruise flight

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