67 research outputs found
ΠΡΠ΅Π½ΠΊΠ° Π²Π»ΠΈΡΠ½ΠΈΡ ΡΡ Π΅ΠΌΡ Β«Π²ΠΈΠ½Ρ Π² ΠΊΠΎΠ»ΡΡΠ΅Β» Π½Π° Π²Π·Π»Π΅ΡΠ½ΡΠ΅ Ρ Π°ΡΠ°ΠΊΡΠ΅ΡΠΈΡΡΠΈΠΊΠΈ Π»Π΅ΡΠ°ΡΠ΅Π»ΡΠ½ΠΎΠ³ΠΎ Π°ΠΏΠΏΠ°ΡΠ°ΡΠ°
ΠΡΠΎΠ°Π½Π°Π»ΡΠ·ΠΎΠ²Π°Π½ΠΎ Π΄Π΅ΡΠΊΡ Π°ΡΠΏΠ΅ΠΊΡΠΈ ΡΠΎΠ·ΡΠ°Ρ
ΡΠ½ΠΊΡ Π°Π΅ΡΠΎΠ΄ΠΈΠ½Π°ΠΌΡΡΠ½ΠΈΡ
Ρ
Π°ΡΠ°ΠΊΡΠ΅ΡΠΈΡΡΠΈΠΊ Π»ΡΡΠ°Π»ΡΠ½ΠΎΠ³ΠΎ Π°ΠΏΠ°ΡΠ°ΡΠ° Π· ΠΏΠΎΠ²ΠΎΡΠΎΡΠ½ΠΈΠΌΠΈ Π³Π²ΠΈΠ½ΡΠ°ΠΌΠΈ Π½Π° ΠΊΡΠ½ΡΡΡ
ΠΊΡΠΈΠ»Π°. ΠΡΠΎΠ²Π΅Π΄Π΅Π½ΠΎ ΠΏΠΎΡΡΠ²Π½ΡΠ½Π½Ρ Π΄Π²ΠΎΡ
Π²ΠΈΠ±ΡΠ°Π½ΠΈΡ
ΠΊΠΎΠΌΠΏΠΎΠ½ΡΠ²Π°Π»ΡΠ½ΠΈΡ
ΡΡ
Π΅ΠΌ. ΠΡΠΈΠ²Π΅Π΄Π΅Π½ΠΎ Π³ΡΠ°ΡΡΡΠ½Ρ Π·Π°Π»Π΅ΠΆΠ½ΠΎΡΡΡ Π·ΠΌΡΠ½ Π°Π΅ΡΠΎΠ΄ΠΈΠ½Π°ΠΌΡΡΠ½ΠΈΡ
ΠΊΠΎΠ΅ΡΡΡΡΡΠ½ΡΡΠ², ΡΡΠ³ΠΎΠ²ΠΈΡ
Ρ
Π°ΡΠ°ΠΊΡΠ΅ΡΠΈΡΡΠΈΠΊ Π³Π²ΠΈΠ½ΡΡΠ² Π΄Π²ΠΎΡ
Π²ΠΈΠ±ΡΠ°Π½ΠΈΡ
ΡΡ
Π΅ΠΌ Π½Π° Π²ΡΡΡ
Π΅ΡΠ°ΠΏΠ°Ρ
Π·Π»ΡΠΎΡΡ Π»ΡΡΠ°ΠΊΠ°.Air transport is the fastest means of transportation. However, for example, doubling cruising speed of flight increases its average ground speed only 10-15%. This is because a lot of time spent on such regimes as takeoff, landing, maneuvering on the ground, and so on. Since the bulk of air traffic is carried away from the 300 to 1000 km, take off and landing can be up to 50% of the length of the flight. So one of the ways to solve pressing tasks outlined is to build an aircraft that combines quality, speed horizontal flight aircraft and helicopters take off and landing. For the first time the technique of calculating aerodynamic characteristics of the aircraft vertical takeoff and landing small size for rational choice of its parameters in order to achieve the required performance testing. We consider a model airplane with rotary screws at the ends of the wings. This combination provides the benefits of a helicopter, namely the possibility of vertical takeoff and landing and hovering at a certain height in the air, with the benefits of the plane - much greater speed and flight range. The main problem of this aircraft is to ensure the stability and controllability during mode transition from vertical to horizontal flight and vice versa. To determine the required parameters propulsion Comparative calculations generated by aircraft with different layout schemes. Research of mass characteristics to determine the advantages and disadvantages of each scheme. The materials performed the study, the results of calculations of aerodynamic characteristics of the designed aircraft vertical takeoff and landing at different tilt angles of attack and thrust vector and at a speed of zero to switch to horizontal flight.ΠΡΠΎΠ°Π½Π°Π»ΠΈΠ·ΠΈΡΠΎΠ²Π°Π½Ρ Π½Π΅ΠΊΠΎΡΠΎΡΡΠ΅ Π°ΡΠΏΠ΅ΠΊΡΡ ΡΠ°ΡΡΠ΅ΡΠ° Π°ΡΡΠΎΠ΄ΠΈΠ½Π°ΠΌΠΈΡΠ΅ΡΠΊΠΈΡ
Ρ
Π°ΡΠ°ΠΊΡΠ΅ΡΠΈΡΡΠΈΠΊ Π»Π΅ΡΠ°ΡΠ΅Π»ΡΠ½ΠΎΠ³ΠΎ Π°ΠΏΠΏΠ°ΡΠ°ΡΠ° Ρ ΠΏΠΎΠ²ΠΎΡΠΎΡΠ½ΡΠΌΠΈ Π²ΠΈΠ½ΡΠ°ΠΌΠΈ Π½Π° ΠΊΠΎΠ½ΡΠ°Ρ
ΠΊΡΡΠ»Π°. ΠΡΠΎΠ²Π΅Π΄Π΅Π½ΠΎ ΡΡΠ°Π²Π½Π΅Π½ΠΈΠ΅ Π΄Π²ΡΡ
Π²ΡΠ±ΡΠ°Π½Π½ΡΡ
ΠΊΠΎΠΌΠΏΠΎΠ½ΠΎΠ²ΠΎΡΠ½ΡΡ
ΡΡ
Π΅ΠΌ. ΠΡΠΈΠ²Π΅Π΄Π΅Π½Ρ Π³ΡΠ°ΡΠΈΡΠ΅ΡΠΊΠΈΠ΅ Π·Π°Π²ΠΈΡΠΈΠΌΠΎΡΡΠΈ ΠΈΠ·ΠΌΠ΅Π½Π΅Π½ΠΈΡ Π°ΡΡΠΎΠ΄ΠΈΠ½Π°ΠΌΠΈΡΠ΅ΡΠΊΠΈΡ
ΠΊΠΎΡΡΡΠΈΡΠΈΠ΅Π½ΡΠΎΠ², ΡΡΠ³ΠΎΠ²ΡΡ
Ρ
Π°ΡΠ°ΠΊΡΠ΅ΡΠΈΡΡΠΈΠΊ Π²ΠΈΠ½ΡΠΎΠ² Π΄Π²ΡΡ
Π²ΡΠ±ΡΠ°Π½Π½ΡΡ
ΡΡ
Π΅ΠΌ Π½Π° Π²ΡΠ΅Ρ
ΡΡΠ°ΠΏΠ°Ρ
Π²Π·Π»Π΅ΡΠ° ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ°
ΠΡΠΎΠ±Π΅Π½Π½ΠΎΡΡΠΈ Π½ΠΈΠ²Π΅Π»ΠΈΡΠΎΠ²ΠΊΠΈ ΡΠ°ΠΌΠΎΠ»Π΅ΡΠΎΠ² Ρ ΠΏΠΎΠΌΠΎΡΡΡ Π»Π°Π·Π΅ΡΠ½ΠΎΠΉ ΠΊΠΎΠΎΡΠ΄ΠΈΠ½Π°ΡΠ½ΠΎ-ΠΈΠ·ΠΌΠ΅ΡΠΈΡΠ΅Π»ΡΠ½ΠΎΠΉ ΠΌΠ°ΡΠΈΠ½Ρ
Π£ ΡΡΠ°ΡΡΡ ΠΏΠΎΠ΄Π°Π½ΠΎ ΠΎΡΠ½ΠΎΠ²Π½Ρ ΠΌΠΎΠΆΠ»ΠΈΠ²ΠΎΡΡΡ ΡΠ° ΠΏΠ΅ΡΠ΅Π²Π°Π³ΠΈ Π½ΡΠ²Π΅Π»ΡΠ²Π°Π½Π½Ρ Π· Π²ΠΈΠΊΠΎΡΠΈΡΡΠ°Π½Π½ΡΠΌ Π»Π°Π·Π΅ΡΠ½ΠΈΡ
ΠΊΠΎΠΎΡΠ΄ΠΈΠ½Π°ΡΠ½ΠΎ-Π²ΠΈΠΌΡΡΡΠ²Π°Π»ΡΠ½ΠΈΡ
ΡΠΈΡΡΠ΅ΠΌ. ΠΠ°ΠΏΡΠΎΠΏΠΎΠ½ΠΎΠ²Π°Π½ΠΎ ΡΠΏΠΎΡΡΠ± ΠΏΡΠΎΠ²Π΅Π΄Π΅Π½Π½Ρ Β«ΠΌΠ°ΡΠ΅ΠΌΠ°ΡΠΈΡΠ½ΠΎΠ³ΠΎ Π²ΠΈΡΡΠ²Π½ΡΠ²Π°Π½Π½ΡΒ», ΠΏΡΠΈ Π·Π°ΡΡΠΎΡΡΠ²Π°Π½Π½Ρ ΡΠΊΠΎΠ³ΠΎ ΡΠΏΠΎΡΠ°ΡΠΊΡ Π·Π΄ΡΠΉΡΠ½ΡΡΡΡΡΡ ΠΎΠ±ΡΠΈΡΠ»Π΅Π½Π½Ρ ΠΏΠ°ΡΠ°ΠΌΠ΅ΡΡΡΠ² ΡΠΈΡΡΠ΅ΠΌΠΈ ΠΊΠΎΠΎΡΠ΄ΠΈΠ½Π°Ρ Π»ΡΡΠ°ΠΊΠ° ΠΏΡΠΈ ΠΏΠ΅ΡΠ΅Ρ
ΠΎΠ΄Ρ Π²ΡΠ΄ ΡΠΈΡΡΠ΅ΠΌΠΈ ΠΊΠΎΠΎΡΠ΄ΠΈΠ½Π°Ρ, Π² ΡΠΊΡΠΉ ΠΏΡΠΎΠ²ΠΎΠ΄ΠΈΠ»ΠΎΡΡ Π²ΠΈΠΌΡΡΡΠ²Π°Π½Π½Ρ, Ρ ΠΏΡΡΠ»Ρ ΡΡΠΎΠ³ΠΎ ΡΠΎΠ±ΠΈΡΡΡΡ ΠΏΠ΅ΡΠ΅ΡΠ°Ρ
ΡΠ½ΠΎΠΊ ΠΊΠΎΠΎΡΠ΄ΠΈΠ½Π°Ρ Π²ΠΈΠΌΡΡΡΠ½ΠΈΡ
ΡΠΎΡΠΎΠΊ Π² Π΄Π°Π½Ρ ΡΠΈΡΡΠ΅ΠΌΡ ΠΊΠΎΠΎΡΠ΄ΠΈΠ½Π°Ρ. Π¦Π΅ Π΄ΠΎΠ·Π²ΠΎΠ»ΡΡ ΡΠ½ΠΈΠΊΠ°ΡΠΈ Π½Π΅ΠΎΠ±Ρ
ΡΠ΄Π½ΠΎΡΡΡ ΡΠΎΡΠ½ΠΎΠ³ΠΎ Π²ΡΡΠ°Π½ΠΎΠ²Π»Π΅Π½Π½Ρ Π»ΡΡΠ°ΠΊΠ° Π² Π³ΠΎΡΠΈΠ·ΠΎΠ½ΡΠ°Π»ΡΠ½Π΅ ΠΏΠΎΠ»ΠΎΠΆΠ΅Π½Π½Ρ. ΠΡΠΎΠ°Π½Π°Π»ΡΠ·ΠΎΠ²Π°Π½ΠΎ Π½ΠΎΠ²Ρ ΠΌΠΎΠΆΠ»ΠΈΠ²ΠΎΡΡΡ Π°Π½Π°Π»ΡΠ·Ρ Π΄Π΅ΡΠΎΡΠΌΠ°ΡΡΠΉ ΠΏΠΎΠ²Π΅ΡΡ
ΠΎΠ½Ρ Π·Π°Π²Π΄ΡΠΊΠΈ ΡΠ²ΠΈΠ΄ΠΊΠΎΠΌΡ ΠΎΠ±ΠΌΡΡΡ Π²Π΅Π»ΠΈΠΊΠΎΡ ΠΊΡΠ»ΡΠΊΠΎΡΡΡ ΡΠΎΡΠΎΠΊ ΠΏΠΎΠ²Π΅ΡΡ
Π½Ρ Π°Π³ΡΠ΅Π³Π°ΡΡ, Π½Π° ΠΎΡΠ½ΠΎΠ²Ρ ΡΠΊΠΈΡ
Π³Π΅Π½Π΅ΡΡΡΡΡΡΡ Π½ΠΎΠ²Π° Π΅Π»Π΅ΠΊΡΡΠΎΠ½Π½Π° ΠΌΠΎΠ΄Π΅Π»Ρ ΡΠ°ΠΊΡΠΈΡΠ½ΠΎΡ Π³Π΅ΠΎΠΌΠ΅ΡΡΡΡ ΠΎΠ±βΡΠΊΡΠ° Π΄Π»Ρ ΠΏΡΠΎΠ²Π΅Π΄Π΅Π½Π½Ρ Π°Π΅ΡΠΎΠ΄ΠΈΠ½Π°ΠΌΡΡΠ½ΠΈΡ
Π΄ΠΎΡΠ»ΡΠ΄ΠΆΠ΅Π½Ρ.The paper presents the main features and benefits of rigging check by means of laser coordinate measuring systems. One of the main features is that it occurs during the measurement processing the three-dimensional coordinates of points, whereas during the normal rigging check - the distance between the projections of the points on the vertical or horizontal plane. Introduced a three-dimensional cartesian coordinate system relative to which measurements are performed. Proposed a method of carrying out a "mathematical alignment", which first calculates the parameters of the airplane coordinate system in the transition from a system of coordinates in which the measurements were made, and then recalculate the coordinates of the measured points in a new coordinate system. This allows to avoid the need for ascertaining the aircraft in a horizontal position. The paper analyzes the new possibilities of deformation analysis of surfaces with quick measurement of a large number of points on the unitβs surface, which is generated on the basis of a new object actual geometry electronic model for aerodynamic researches.Π ΡΡΠ°ΡΡΠ΅ ΠΏΡΠ΅Π΄ΡΡΠ°Π²Π»Π΅Π½Ρ ΠΎΡΠ½ΠΎΠ²Π½ΡΠ΅ Π²ΠΎΠ·ΠΌΠΎΠΆΠ½ΠΎΡΡΠΈ ΠΈ ΠΏΡΠ΅ΠΈΠΌΡΡΠ΅ΡΡΠ²Π° Π½ΠΈΠ²Π΅Π»ΠΈΡΠΎΠ²Π°Π½ΠΈΡ Ρ ΠΈΡΠΏΠΎΠ»ΡΠ·ΠΎΠ²Π°Π½ΠΈΠ΅ΠΌ Π»Π°Π·Π΅ΡΠ½ΡΡ
ΠΊΠΎΠΎΡΠ΄ΠΈΠ½Π°ΡΠ½ΠΎ-ΠΈΠ·ΠΌΠ΅ΡΠΈΡΠ΅Π»ΡΠ½ΡΡ
ΡΠΈΡΡΠ΅ΠΌ. ΠΡΠ΅Π΄Π»ΠΎΠΆΠ΅Π½ ΡΠΏΠΎΡΠΎΠ± ΠΏΡΠΎΠ²Π΅Π΄Π΅Π½ΠΈΡ Β«ΠΌΠ°ΡΠ΅ΠΌΠ°ΡΠΈΡΠ΅ΡΠΊΠΎΠ³ΠΎ Π²ΡΡΠ°Π²Π½ΠΈΠ²Π°Π½ΠΈΡΒ», ΠΏΡΠΈ ΠΏΡΠΈΠΌΠ΅Π½Π΅Π½ΠΈΠΈ ΠΊΠΎΡΠΎΡΠΎΠ³ΠΎ ΡΠ½Π°ΡΠ°Π»Π° ΠΏΡΠΎΠΈΠ·Π²ΠΎΠ΄ΠΈΡΡΡ ΠΎΠΏΡΠ΅Π΄Π΅Π»Π΅Π½ΠΈΠ΅ ΠΏΠ°ΡΠ°ΠΌΠ΅ΡΡΠΎΠ² ΡΠΈΡΡΠ΅ΠΌΡ ΠΊΠΎΠΎΡΠ΄ΠΈΠ½Π°Ρ ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ° ΠΏΡΠΈ ΠΏΠ΅ΡΠ΅Ρ
ΠΎΠ΄Π΅ ΠΎΡ ΡΠΈΡΡΠ΅ΠΌΡ ΠΊΠΎΠΎΡΠ΄ΠΈΠ½Π°Ρ, Π² ΠΊΠΎΡΠΎΡΠΎΠΉ ΠΏΡΠΎΠ²ΠΎΠ΄ΠΈΠ»ΠΎΡΡ ΠΈΠ·ΠΌΠ΅ΡΠ΅Π½ΠΈΠ΅, ΠΈ ΠΏΠΎΡΠ»Π΅ ΡΡΠΎΠ³ΠΎ ΠΎΡΡΡΠ΅ΡΡΠ²Π»ΡΠ΅ΡΡΡ ΠΏΠ΅ΡΠ΅ΡΡΠ΅Ρ ΠΊΠΎΠΎΡΠ΄ΠΈΠ½Π°Ρ ΠΈΠ·ΠΌΠ΅ΡΠ΅Π½Π½ΡΡ
ΡΠΎΡΠ΅ΠΊ Π² Π΄Π°Π½Π½ΡΡ ΡΠΈΡΡΠ΅ΠΌΡ ΠΊΠΎΠΎΡΠ΄ΠΈΠ½Π°Ρ. ΠΡΠΎ ΠΏΠΎΠ·Π²ΠΎΠ»ΡΠ΅Ρ ΠΈΠ·Π±Π΅ΠΆΠ°ΡΡ Π½Π΅ΠΎΠ±Ρ
ΠΎΠ΄ΠΈΠΌΠΎΡΡΠΈ ΡΠΎΡΠ½ΠΎΠ³ΠΎ ΡΡΡΠ°Π½ΠΎΠ²Π»Π΅Π½ΠΈΡ ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ° Π² Π³ΠΎΡΠΈΠ·ΠΎΠ½ΡΠ°Π»ΡΠ½ΠΎΠ΅ ΠΏΠΎΠ»ΠΎΠΆΠ΅Π½ΠΈΠ΅. ΠΡΠΎΠ°Π½Π°Π»ΠΈΠ·ΠΈΡΠΎΠ²Π°Π½Ρ Π½ΠΎΠ²ΡΠ΅ Π²ΠΎΠ·ΠΌΠΎΠΆΠ½ΠΎΡΡΠΈ Π°Π½Π°Π»ΠΈΠ·Π° Π΄Π΅ΡΠΎΡΠΌΠ°ΡΠΈΠΉ ΠΏΠΎΠ²Π΅ΡΡ
Π½ΠΎΡΡΠ΅ΠΉ Π±Π»Π°Π³ΠΎΠ΄Π°ΡΡ Π±ΡΡΡΡΠΎΠΌΡ ΠΎΠ±ΠΌΠ΅ΡΡ Π±ΠΎΠ»ΡΡΠΎΠ³ΠΎ ΠΊΠΎΠ»ΠΈΡΠ΅ΡΡΠ²Π° ΡΠΎΡΠ΅ΠΊ ΠΏΠΎΠ²Π΅ΡΡ
Π½ΠΎΡΡΠΈ Π°Π³ΡΠ΅Π³Π°ΡΠ°, Π½Π° ΠΎΡΠ½ΠΎΠ²Π΅ ΠΊΠΎΡΠΎΡΡΡ
Π³Π΅Π½Π΅ΡΠΈΡΡΠ΅ΡΡΡ Π½ΠΎΠ²Π°Ρ ΡΠ»Π΅ΠΊΡΡΠΎΠ½Π½Π°Ρ ΠΌΠΎΠ΄Π΅Π»Ρ ΡΠ°ΠΊΡΠΈΡΠ΅ΡΠΊΠΎΠΉ Π³Π΅ΠΎΠΌΠ΅ΡΡΠΈΠΈ ΠΎΠ±ΡΠ΅ΠΊΡΠ° Π΄Π»Ρ ΠΏΡΠΎΠ²Π΅Π΄Π΅Π½ΠΈΡ Π°ΡΡΠΎΠ΄ΠΈΠ½Π°ΠΌΠΈΡΠ΅ΡΠΊΠΈΡ
ΠΈΡΡΠ»Π΅Π΄ΠΎΠ²Π°Π½ΠΈΠΉ
ΠΠΎΠΌΠΏΡΡΡΠ΅ΡΠ½ΠΎΠ΅ ΠΌΠΎΠ΄Π΅Π»ΠΈΡΠΎΠ²Π°Π½ΠΈΠ΅ Π±Π°Π·ΠΎΠ²ΠΎΠΉ Π³Π΅ΠΎΠΌΠ΅ΡΡΠΈΠΈ ΠΊΡΡΠ»Π° ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ°
Π£ ΡΡΠ°ΡΡΡ ΠΏΡΠΎΠ°Π½Π°Π»ΡΠ·ΠΎΠ²Π°Π½ΠΎ Π΄Π΅ΡΠΊΡ Π°ΡΠΏΠ΅ΠΊΡΠΈ Π²Π°ΡΡΠ°Π½ΡΠ½ΠΎΠ³ΠΎ ΠΌΠΎΠ΄Π΅Π»ΡΠ²Π°Π½Π½Ρ Π±Π°Π·ΠΎΠ²ΠΎΡ Π³Π΅ΠΎΠΌΠ΅ΡΡΡΡ ΠΊΡΠΈΠ»Π° Π»ΡΡΠ°ΠΊΠ°. ΠΠ°ΠΏΡΠΎΠΏΠΎΠ½ΠΎΠ²Π°Π½ΠΎ Π½ΠΎΠ²Ρ ΡΠΏΠΎΡΠΎΠ±ΠΈ ΡΠ° ΠΏΡΠΈΠΉΠΎΠΌΠΈ ΡΠ½ΡΠ΅Π³ΡΠΎΠ²Π°Π½ΠΎΠ³ΠΎ ΡΠΎΡΠΌΠΎΡΡΠ²ΠΎΡΠ΅Π½Π½Ρ Π² ΡΠ΅ΡΠ΅Π΄ΠΎΠ²ΠΈΡΡ ΡΡΡΠ°ΡΠ½ΠΈΡ
ΡΠΈΡΡΠ΅ΠΌ Π°Π²ΡΠΎΠΌΠ°ΡΠΈΠ·ΠΎΠ²Π°Π½ΠΎΠ³ΠΎ ΠΏΡΠΎΠ΅ΠΊΡΡΠ²Π°Π½Π½Ρ, Π½Π°Π²Π΅Π΄Π΅Π½ΠΎ Π²ΡΠ΄ΠΏΠΎΠ²ΡΠ΄Π½Ρ ΡΠ»ΡΡΡΡΠ°ΡΠΈΠ²Π½Ρ ΠΏΡΠΈΠΊΠ»Π°Π΄ΠΈ. ΠΠΈΠΊΠΎΠ½Π°Π½ΠΎ ΡΠ·Π°Π³Π°Π»ΡΠ½Π΅Π½Π½Ρ ΡΡΠΎΡΠΎΠ²Π½ΠΎ ΠΏΠ΅ΡΡΠΏΠ΅ΠΊΡΠΈΠ² ΠΏΡΠ°ΠΊΡΠΈΡΠ½ΠΎΠ³ΠΎ Π²ΠΏΡΠΎΠ²Π°Π΄ΠΆΠ΅Π½Π½Ρ ΠΎΡΡΠΈΠΌΠ°Π½ΠΈΡ
ΡΠ΅Π·ΡΠ»ΡΡΠ°ΡΡΠ², ΡΡ
Π·Π°ΡΡΠΎΡΡΠ²Π°Π½Π½Ρ Π² ΠΏΠΎΠ΄Π°Π»ΡΡΠΈΡ
Π½Π°ΡΠΊΠΎΠ²ΠΈΡ
Π΄ΠΎΡΠ»ΡΠ΄ΠΆΠ΅Π½Π½ΡΡ
ΡΠΎΠ΄ΠΎ ΠΊΠΎΠΌΠΏβΡΡΠ΅ΡΠ½ΠΎΠ³ΠΎ ΠΎΠΏΡΠ°ΡΡΠ²Π°Π½Π½Ρ Π°Π²ΡΠ°ΡΡΠΉΠ½ΠΎΡ ΡΠ΅Ρ
Π½ΡΠΊΠΈ.The paper analyzes some aspects of the variant modeling for basic geometry of airplane wing. These data include information on the theoretical external surfaces of the airplane, the location of such elements of its design-force elements as spars, ribs and stringers of wing, etc. The basic geometry is the foundation for subsequent automated design of airplane and also for creation technological processes of its manufacture and use. New ways and methods of integrated forming in the environment of modern CAD systems have been proposed. They are based on extensive use of information technology databases, flexible performing alternative calculations and the correct implementation of the geometric modeling of technical objects in the environment of modern computer-aided design. OpenOffice Calc spreadsheets and CAD SolidWorks were taken to carry out related research. Database of aerodynamic profiles and basic geometry of the wing was set up in the environment of the first software package. Automated communication geometric wing database with other software for its design has been installed. The corresponding geometric relationship database wing and SolidWorks CAD has been implemented. This technique allows an automated way to create and analyze multiple design variants of the airplane wing. The specified method significantly improves the quality of created technical objects. The laboriousness of design work is also reduced. This is achieved by through automation of all design operations. Illustrative examples in the environment OpenOffice Calc spreadsheets and SoidWorks CAD are given in this article. Calculation formulas to populate of database fields are shown. Questions relationship base geometry of the wing and its strength, design, technology, manufacturing and operation are analyzed. The proposed technique can be used as part of the general methodology of complex automation of the aircraft throughout its life cycle. Summary of the practical implementation of the results and their use in further research in the field of computer design of airplane has been completed.Π ΡΡΠ°ΡΡΠ΅ ΠΏΡΠΎΠ°Π½Π°Π»ΠΈΠ·ΠΈΡΠΎΠ²Π°Π½Ρ Π½Π΅ΠΊΠΎΡΠΎΡΡΠ΅ Π°ΡΠΏΠ΅ΠΊΡΡ Π²Π°ΡΠΈΠ°Π½ΡΠ½ΠΎΠ³ΠΎ ΠΌΠΎΠ΄Π΅Π»ΠΈΡΠΎΠ²Π°Π½ΠΈΡ Π±Π°Π·ΠΎΠ²ΠΎΠΉ Π³Π΅ΠΎΠΌΠ΅ΡΡΠΈΠΈ ΠΊΡΡΠ»Π° ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ°. ΠΡΠ΅Π΄Π»ΠΎΠΆΠ΅Π½Ρ Π½ΠΎΠ²ΡΠ΅ ΡΠΏΠΎΡΠΎΠ±Ρ ΠΈ ΠΏΡΠΈΠ΅ΠΌΡ ΠΈΠ½ΡΠ΅Π³ΡΠΈΡΠΎΠ²Π°Π½Π½ΠΎΠ³ΠΎ ΡΠΎΡΠΌΠΎΠΎΠ±ΡΠ°Π·ΠΎΠ²Π°Π½ΠΈΡ Π² ΡΡΠ΅Π΄Π΅ ΡΠΎΠ²ΡΠ΅ΠΌΠ΅Π½Π½ΡΡ
ΡΠΈΡΡΠ΅ΠΌ Π°Π²ΡΠΎΠΌΠ°ΡΠΈΠ·ΠΈΡΠΎΠ²Π°Π½Π½ΠΎΠ³ΠΎ ΠΏΡΠΎΠ΅ΠΊΡΠΈΡΠΎΠ²Π°Π½ΠΈΡ, ΠΏΡΠΈΠ²Π΅Π΄Π΅Π½Ρ ΡΠΎΠΎΡΠ²Π΅ΡΡΡΠ²ΡΡΡΠΈΠ΅ ΠΈΠ»Π»ΡΡΡΡΠ°ΡΠΈΠ²Π½ΡΠ΅ ΠΏΡΠΈΠΌΠ΅ΡΡ. ΠΡΠΏΠΎΠ»Π½Π΅Π½Ρ ΠΎΠ±ΠΎΠ±ΡΠ΅Π½ΠΈΡ ΠΎΡΠ½ΠΎΡΠΈΡΠ΅Π»ΡΠ½ΠΎ ΠΏΠ΅ΡΡΠΏΠ΅ΠΊΡΠΈΠ² ΠΏΡΠ°ΠΊΡΠΈΡΠ΅ΡΠΊΠΎΠ³ΠΎ Π²Π½Π΅Π΄ΡΠ΅Π½ΠΈΡ ΠΏΠΎΠ»ΡΡΠ΅Π½Π½ΡΡ
ΡΠ΅Π·ΡΠ»ΡΡΠ°ΡΠΎΠ², ΠΈΡ
ΠΏΡΠΈΠΌΠ΅Π½Π΅Π½ΠΈΡ Π² Π΄Π°Π»ΡΠ½Π΅ΠΉΡΠΈΡ
Π½Π°ΡΡΠ½ΡΡ
ΠΈΡΡΠ»Π΅Π΄ΠΎΠ²Π°Π½ΠΈΡΡ
Π² ΠΎΠ±Π»Π°ΡΡΠΈ ΠΊΠΎΠΌΠΏΡΡΡΠ΅ΡΠ½ΠΎΠΉ ΡΠ°Π·ΡΠ°Π±ΠΎΡΠΊΠΈ Π°Π²ΠΈΠ°ΡΠΈΠΎΠ½Π½ΠΎΠΉ ΡΠ΅Ρ
Π½ΠΈΠΊΠΈ
ΠΠ»Π³ΠΎΡΠΈΡΠΌ Π°Π²ΡΠΎΠΌΠ°ΡΠΈΠ·ΠΈΡΠΎΠ²Π°Π½Π½ΠΎΠ³ΠΎ ΡΠΎΡΠΌΠΈΡΠΎΠ²Π°Π½ΠΈΡ ΠΊΠΎΠ½Π΅ΡΠ½ΠΎ-ΡΠ»Π΅ΠΌΠ΅Π½ΡΠ½ΠΎΠΉ ΠΌΠΎΠ΄Π΅Π»ΠΈ ΡΠΈΠ»ΠΎΠ²ΠΎΠ³ΠΎ ΡΠΏΠ°Π½Π³ΠΎΡΡΠ° ΡΡΠ·Π΅Π»ΡΠΆΠ° ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ°
ΠΡΠΈ ΡΠΎΡΠΌΡΠ²Π°Π½Π½Ρ ΠΊΡΠ½ΡΠ΅Π²ΠΎ-Π΅Π»Π΅ΠΌΠ΅Π½ΡΠ½ΠΈΡ
ΠΌΠΎΠ΄Π΅Π»Π΅ΠΉ ΠΊΠΎΠ½ΡΡΡΡΠΊΡΡΡ Π²ΠΈΠ½ΠΈΠΊΠ°Ρ Π·Π°Π²Π΄Π°Π½Π½Ρ Π·Π½ΠΈΠΆΠ΅Π½Π½Ρ ΡΠ°ΡΡ ΠΏΡΠΎΠ΅ΠΊΡΡΠ²Π°Π½Π½Ρ. ΠΠ°ΠΉΠ±ΡΠ»ΡΡ Π΅ΡΠ΅ΠΊΡΠΈΠ²Π½ΠΎ ΡΡ ΠΏΠΈΡΠ°Π½Π½Ρ Π²ΠΈΡΡΡΡΡΡΡΡΡ Π·Π° Π΄ΠΎΠΏΠΎΠΌΠΎΠ³ΠΎΡ Π°Π²ΡΠΎΠΌΠ°ΡΠΈΠ·ΠΎΠ²Π°Π½ΠΈΡ
ΡΠ½ΡΠΎΡΠΌΠ°ΡΡΠΉΠ½ΠΈΡ
ΡΠ΅Ρ
Π½ΠΎΠ»ΠΎΠ³ΡΠΉ. ΠΠ»Ρ ΡΡΠΏΡΡΠ½ΠΎΡ ΡΠ΅Π°Π»ΡΠ·Π°ΡΡΡ ΠΎΡΡΠ°Π½Π½ΡΡ
ΠΏΠΎΡΡΡΠ±Π½Ρ Π°Π»Π³ΠΎΡΠΈΡΠΌΠΈ ΡΠΎΠ·Π²'ΡΠ·ΡΠ²Π°Π½Π½Ρ ΠΏΠΎΡΡΠ°Π²Π»Π΅Π½ΠΈΡ
Π·Π°Π΄Π°Ρ, Π½Π° ΠΏΡΠ΄ΡΡΠ°Π²Ρ ΡΠΊΠΈΡ
ΡΠΎΠ·ΡΠΎΠ±Π»ΡΡΡΡΡΡ Π²ΡΠ΄ΠΏΠΎΠ²ΡΠ΄Π½Ρ ΠΌΠ΅ΡΠΎΠ΄ΠΈ ΠΉ Π·Π°ΡΠΎΠ±ΠΈ ΠΌΠΎΠ΄Π΅Π»ΡΠ²Π°Π½Π½Ρ. ΠΠ°ΠΏΡΠΎΠΏΠΎΠ½ΠΎΠ²Π°Π½ΠΎ Π°Π»Π³ΠΎΡΠΈΡΠΌ Π°Π²ΡΠΎΠΌΠ°ΡΠΈΠ·ΠΎΠ²Π°Π½ΠΎΠ³ΠΎ ΡΠΎΡΠΌΡΠ²Π°Π½Π½Ρ ΡΡΡΡΠΊΡΡΡΠΈ ΠΊΡΠ½ΡΠ΅Π²ΠΎ-Π΅Π»Π΅ΠΌΠ΅Π½ΡΠ½ΠΎΡ ΠΌΠΎΠ΄Π΅Π»Ρ ΡΠΈΠ»ΠΎΠ²ΠΎΠ³ΠΎ ΡΠΏΠ°Π½Π³ΠΎΡΡΠ° ΡΡΠ·Π΅Π»ΡΠΆΡ. Π ΠΎΠ·ΡΠΎΠ±Π»Π΅Π½ΠΈΠΉ Π°Π»Π³ΠΎΡΠΈΡΠΌ Ρ ΡΠ½ΡΠ²Π΅ΡΡΠ°Π»ΡΠ½ΠΈΠΌ, ΠΎΡΠΊΡΠ»ΡΠΊΠΈ Π½Π΅ Π·Π°Π»Π΅ΠΆΠΈΡΡ Π²ΡΠ΄ ΠΊΠΎΠ½ΡΡΠ³ΡΡΠ°ΡΡΡ ΠΊΠΎΠ½ΠΊΡΠ΅ΡΠ½ΠΎΡ ΠΏΡΠΎΠ΅ΠΊΡΠΎΠ²Π°Π½ΠΎΡ ΠΊΠΎΠ½ΡΡΡΡΠΊΡΡΡ. Π’ΠΎΠΌΡ Π²ΡΠ½ ΠΌΠΎΠΆΠ΅ Π±ΡΡΠΈ Π²ΠΈΠΊΠΎΡΠΈΡΡΠ°Π½ΠΈΠΉ ΠΏΡΠ΄ ΡΠ°Ρ ΠΏΡΠΎΠ΅ΠΊΡΡΠ²Π°Π½Π½Ρ ΡΠΏΠ°Π½Π³ΠΎΡΡΡΠ² Π»ΡΡΠ°ΠΊΡΠ² ΡΡΠ·Π½ΠΈΡ
ΠΊΠ»Π°ΡΡΠ².Design and processing power circuits aircraft is a problem of structural and parametric synthesis includes an analysis of possible variants of these schemes and their determination of the optimal parameters. Complications constructive power circuits aircraft and growth requirements for the quality of their design has led to the application of the finite element method. This method allows to accurately model complex structures, to determine the stress-strain state and to automate the processes of synthesis in selecting schemes, but because of the great complexity and duration of the set-up cycle before widely used only in the later stages of the design During formation of certainly-element models of construction arises to reduce design time. The most effective issues of these questions are addressed using automated technologies. For successful implementation of the latest needed algorithms for solving the tasks on which developed appropriate methods and means of simulation. The choice of algorithm is part of the design process, as design problems belong to a class of inverse problems. For this reason, a list of the algorithms can not be determined in advance. As a result, it is necessary to select and connect directly to the algorithms in the solution of the problem (dynamic link algorithms). The purpose of this paper is to develop an automated algorithm forming the structure of the finite element model of the power of frame fuselage. In this paper an automatic algorithm of formation of the structure certainly-element model force fuselage frame. The structure of the finite-element model is synthesized simultaneously with the creation of the appropriate subobject through its automatic activation. The parameters of this structure must be passed on to the class object fuselage for the synthesis of the finite-element model. In the design process by KCC considered algorithm, the user can create the required number of settlement CEM frames. The algorithm is universal, because it depends on the specific configuration of the designed construction. Therefore, it can be used in the design of aircraft frames of different classes.ΠΡΠΈ ΡΠΎΡΠΌΠΈΡΠΎΠ²Π°Π½ΠΈΠΈ ΠΊΠΎΠ½Π΅ΡΠ½ΠΎ-ΡΠ»Π΅ΠΌΠ΅Π½ΡΠ½ΡΡ
ΠΌΠΎΠ΄Π΅Π»Π΅ΠΉ ΠΊΠΎΠ½ΡΡΡΡΠΊΡΠΈΠΈ Π²ΠΎΠ·Π½ΠΈΠΊΠ°Π΅Ρ Π·Π°Π΄Π°ΡΠ° ΡΠ½ΠΈΠΆΠ΅Π½ΠΈΡ Π²ΡΠ΅ΠΌΠ΅Π½ΠΈ ΠΏΡΠΎΠ΅ΠΊΡΠΈΡΠΎΠ²Π°Π½ΠΈΡ. ΠΠ°ΠΈΠ±ΠΎΠ»Π΅Π΅ ΡΡΡΠ΅ΠΊΡΠΈΠ²Π½ΠΎ ΡΡΠΈ Π²ΠΎΠΏΡΠΎΡΡ ΡΠ΅ΡΠ°ΡΡΡΡ Ρ ΠΏΠΎΠΌΠΎΡΡΡ Π°Π²ΡΠΎΠΌΠ°ΡΠΈΠ·ΠΈΡΠΎΠ²Π°Π½Π½ΡΡ
ΠΈΠ½ΡΠΎΡΠΌΠ°ΡΠΈΠΎΠ½Π½ΡΡ
ΡΠ΅Ρ
Π½ΠΎΠ»ΠΎΠ³ΠΈΠΉ. ΠΠ»Ρ ΡΡΠΏΠ΅ΡΠ½ΠΎΠΉ ΡΠ΅Π°Π»ΠΈΠ·Π°ΡΠΈΠΈ ΠΏΠΎΡΠ»Π΅Π΄Π½ΠΈΡ
ΡΡΠ΅Π±ΡΡΡΡΡ Π°Π»Π³ΠΎΡΠΈΡΠΌΡ ΡΠ΅ΡΠ΅Π½ΠΈΡ ΠΏΠΎΡΡΠ°Π²Π»Π΅Π½Π½ΡΡ
Π·Π°Π΄Π°Ρ, Π½Π° ΠΎΡΠ½ΠΎΠ²Π°Π½ΠΈΠΈ ΠΊΠΎΡΠΎΡΡΡ
ΡΠ°Π·ΡΠ°Π±Π°ΡΡΠ²Π°ΡΡΡΡ ΡΠΎΠΎΡΠ²Π΅ΡΡΡΠ²ΡΡΡΠΈΠ΅ ΠΌΠ΅ΡΠΎΠ΄Ρ ΠΈ ΡΡΠ΅Π΄ΡΡΠ²Π° ΠΌΠΎΠ΄Π΅Π»ΠΈΡΠΎΠ²Π°Π½ΠΈΡ. Π ΡΡΠ°ΡΡΠ΅ ΠΏΡΠ΅Π΄Π»ΠΎΠΆΠ΅Π½ Π°Π»Π³ΠΎΡΠΈΡΠΌ Π°Π²ΡΠΎΠΌΠ°ΡΠΈΠ·ΠΈΡΠΎΠ²Π°Π½Π½ΠΎΠ³ΠΎ ΡΠΎΡΠΌΠΈΡΠΎΠ²Π°Π½ΠΈΡ ΡΡΡΡΠΊΡΡΡΡ ΠΊΠΎΠ½Π΅ΡΠ½ΠΎ-ΡΠ»Π΅ΠΌΠ΅Π½ΡΠ½ΠΎΠΉ ΠΌΠΎΠ΄Π΅Π»ΠΈ ΡΠΈΠ»ΠΎΠ²ΠΎΠ³ΠΎ ΡΠΏΠ°Π½Π³ΠΎΡΡΠ° ΡΡΠ·Π΅Π»ΡΠΆΠ°. Π Π°Π·ΡΠ°Π±ΠΎΡΠ°Π½Π½ΡΠΉ Π°Π»Π³ΠΎΡΠΈΡΠΌ ΡΠ²Π»ΡΠ΅ΡΡΡ ΡΠ½ΠΈΠ²Π΅ΡΡΠ°Π»ΡΠ½ΡΠΌ, ΠΏΠΎΡΠΊΠΎΠ»ΡΠΊΡ Π½Π΅ Π·Π°Π²ΠΈΡΠΈΡ ΠΎΡ ΠΊΠΎΠ½ΡΠΈΠ³ΡΡΠ°ΡΠΈΠΈ ΠΊΠΎΠ½ΠΊΡΠ΅ΡΠ½ΠΎΠΉ ΠΏΡΠΎΠ΅ΠΊΡΠΈΡΡΠ΅ΠΌΠΎΠΉ ΠΊΠΎΠ½ΡΡΡΡΠΊΡΠΈΠΈ. ΠΠΎΡΡΠΎΠΌΡ ΠΎΠ½ ΠΌΠΎΠΆΠ΅Ρ Π±ΡΡΡ ΠΈΡΠΏΠΎΠ»ΡΠ·ΠΎΠ²Π°Π½ ΠΏΡΠΈ ΠΏΡΠΎΠ΅ΠΊΡΠΈΡΠΎΠ²Π°Π½ΠΈΠΈ ΡΠΏΠ°Π½Π³ΠΎΡΡΠΎΠ² ΡΠ°ΠΌΠΎΠ»Π΅ΡΠΎΠ² ΡΠ°Π·Π»ΠΈΡΠ½ΡΡ
ΠΊΠ»Π°ΡΡΠΎΠ²
ΠΠ΅ΡΠΎΠ΄ΠΈΠΊΠ° ΠΈΠ½ΡΠ΅Π³ΡΠΈΡΠΎΠ²Π°Π½Π½ΠΎΠ³ΠΎ Π°Π²ΡΠΎΠΌΠ°ΡΠΈΠ·ΠΈΡΠΎΠ²Π°Π½Π½ΠΎΠ³ΠΎ ΠΏΡΠΎΠ΅ΠΊΡΠΈΡΠΎΠ²Π°Π½ΠΈΡ ΡΠ»Π΅ΠΌΠ΅Π½ΡΠΎΠ² ΠΊΠΎΠ½ΡΡΡΡΠΊΡΠΈΠΈ ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ°
Π ΡΡΠ°ΡΡΡ ΡΠΎΠ·Π³Π»ΡΠ½ΡΡΠΎ ΠΏΡΠ΄Ρ
ΠΎΠ΄ΠΈ Π΄ΠΎ ΡΠ½ΡΠ΅Π³ΡΠΎΠ²Π°Π½ΠΎΠ³ΠΎ Π°Π²ΡΠΎΠΌΠ°ΡΠΈΠ·ΠΎΠ²Π°Π½ΠΎΠ³ΠΎ ΠΏΡΠΎΠ΅ΠΊΡΡΠ²Π°Π½Π½Ρ. ΠΠΈΡΠ²ΡΡΠ»Π΅Π½Ρ ΠΏΡΠΎΠ±Π»Π΅ΠΌΠΈ ΠΏΠΎΠΏΠ΅ΡΠ΅Π΄Π½ΡΠΎΠ³ΠΎ ΠΏΡΠΎΠ΅ΠΊΡΡΠ²Π°Π½Π½Ρ ΡΠ° Π·Π°ΠΏΡΠΎΠΏΠΎΠ½ΠΎΠ²Π°Π½ΠΎ ΠΌΠ΅ΡΠΎΠ΄ΠΈΠΊΠΎ ΡΠΎΠ·ΡΠ°Ρ
ΡΠ½ΠΊΡ ΡΠΈΠΏΠΎΠ²ΠΈΡ
Π΅Π»Π΅ΠΌΠ΅Π½ΡΡΠ² ΠΊΠΎΠ½ΡΡΡΡΠΊΡΡΡ Π»ΡΡΠ°ΠΊΠ° Π½Π° ΠΏΡΠΈΠΊΠ»Π°Π΄Ρ Π΅Π»Π΅ΠΌΠ΅Π½ΡΠ° ΠΏΠΎΠ²Π·Π΄ΠΎΠ²ΠΆΠ½ΡΠΎΠ³ΠΎ ΡΠΈΠ»ΠΎΠ²ΠΎΠ³ΠΎ Π½Π°Π±ΠΎΡ, ΡΠΊ ΡΡΡΠΈΠ½Π³Π΅Ρ. Π’Π°ΠΊΠΎΠΆ ΠΏΠΎΠ²Π½ΡΡΡΡ ΠΏΡΠ΅Π΄ΡΡΠ°Π²Π»Π΅Π½ΠΈΠΉ Π°Π»Π³ΠΎΡΠΈΡΠΌ ΠΏΠΎΠ±ΡΠ΄ΠΎΠ² ΡΡΡΠΈΠ½Π³Π΅ΡΠ° Π² ΡΠΈΡΡΠ΅ΠΌΡ ΡΠ½ΡΠ΅Π³ΡΠΎΠ²Π°Π½ΠΎΠ³ΠΎ Π°Π²ΡΠΎΠΌΠ°ΡΠΈΠ·ΠΎΠ²Π°Π½ΠΎΠ³ΠΎ ΠΏΡΠΎΠ΅ΠΊΡΡΠ²Π°Π½Π½Ρ Siemens NX. Π©ΠΎ Π΄ΠΎΠ·Π²ΠΎΠ»ΡΡ ΡΠΊΠΎΡΠΎΡΠΈ ΡΠ°Ρ Π½Π° ΠΏΡΠΎΠ΅ΠΊΡΡΠ²Π°Π½Π½Ρ ΡΠ° Π²ΠΈΠΊΠΎΡΠΈΡΡΠΎΠ²ΡΠ²Π°ΡΠΈ ΠΉΠΎΠ³ΠΎ ΡΠΊ Π΅ΡΠ°Π»ΠΎΠ½ Π΄Π»Ρ ΡΠΎΠ·ΡΠ°Ρ
ΡΠ½ΠΊΡ ΡΠ° ΠΏΠΎΠ΄Π°Π»ΡΡΠΎΠ³ΠΎ Π·ΠΌΡΠ½Π΅Π½Π½Ρ ΠΏΡΠΎΡΡΠΎ Π·Π½Π°ΡΠ΅Π½Ρ Π΄Π»Ρ ΠΎΡΡΠΈΠΌΠ°Π½Π½Ρ ΡΠ½ΡΠΎΡ ΡΠΎΠ·ΠΌΡΡΠ½ΠΎΡΡΡ ΡΡΡΠΈΠ½Π³Π΅ΡΡΠ².Previously applied methods of designing aircraft based on two-dimensional geometric models that made it impossible to take into account all the necessary design and technological features. It was a prerequisite for the development of an integrated methodology that includes design and computer simulation of three-dimensional parametric design of the aircraft as a whole and its individual parts [2-5]. In this paper, the method of computer-aided design stringer at the master model geometry and space allocation wing aircraft. In article approaches to integrated computer-aided design. These types of problems preliminary design and the method of calculation of typical aircraft structural elements for example longitudinal force element sets as stringer. Also, the algorithm constructs a fully stringer system aided design of integrated Siemens NX. What can shorten the design time and use it as a reference for the calculation and further change just values for other dimensions stringers. Methods integrated design ensure the application of standard parametric analytical stringers in the calculation of aerodynamics and strength, life and vitality, weight of the aircraft and its alignment, safety of structures, as well as technological preparation of production and quality control, maintenance and repair. Considered aided design techniques can be extended to other than the stringers typical elements airframe.Π ΡΡΠ°ΡΡΠ΅ ΡΠ°ΡΡΠΌΠΎΡΡΠ΅Π½Ρ ΠΏΠΎΠ΄Ρ
ΠΎΠ΄Ρ ΠΊ ΠΈΠ½ΡΠ΅Π³ΡΠΈΡΠΎΠ²Π°Π½Π½ΠΎΠΌΡ Π°Π²ΡΠΎΠΌΠ°ΡΠΈΠ·ΠΈΡΠΎΠ²Π°Π½Π½ΠΎΠ³ΠΎ ΠΏΡΠΎΠ΅ΠΊΡΠΈΡΠΎΠ²Π°Π½ΠΈΡ. ΠΡΠ²Π΅ΡΠ΅Π½Ρ ΠΏΡΠΎΠ±Π»Π΅ΠΌΡ ΠΏΡΠ΅Π΄Π²Π°ΡΠΈΡΠ΅Π»ΡΠ½ΠΎΠ³ΠΎ ΠΏΡΠΎΠ΅ΠΊΡΠΈΡΠΎΠ²Π°Π½ΠΈΡ ΠΈ ΠΏΡΠ΅Π΄Π»ΠΎΠΆΠ΅Π½Ρ ΠΌΠ΅ΡΠΎΠ΄ΠΈΠΊΠΈ ΡΠ°ΡΡΠ΅ΡΠ° ΡΠΈΠΏΠΎΠ²ΡΡ
ΡΠ»Π΅ΠΌΠ΅Π½ΡΠΎΠ² ΠΊΠΎΠ½ΡΡΡΡΠΊΡΠΈΠΈ ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ° Π½Π° ΠΏΡΠΈΠΌΠ΅ΡΠ΅ ΡΠ»Π΅ΠΌΠ΅Π½ΡΠ° ΠΏΡΠΎΠ΄ΠΎΠ»ΡΠ½ΠΎΠ³ΠΎ ΡΠΈΠ»ΠΎΠ²ΠΎΠ³ΠΎ Π½Π°Π±ΠΎΡ, ΠΊΠ°ΠΊ ΡΡΡΠΈΠ½Π³Π΅Ρ. Π’Π°ΠΊΠΆΠ΅ ΠΏΠΎΠ»Π½ΠΎΡΡΡΡ ΠΏΡΠ΅Π΄ΡΡΠ°Π²Π»Π΅Π½ Π°Π»Π³ΠΎΡΠΈΡΠΌ ΠΏΠΎΡΡΡΠΎΠ΅Π½ΠΈΠΉ ΡΡΡΠΈΠ½Π³Π΅ΡΠ° Π² ΡΠΈΡΡΠ΅ΠΌΠ΅ ΠΈΠ½ΡΠ΅Π³ΡΠΈΡΠΎΠ²Π°Π½Π½ΠΎΠ³ΠΎ Π°Π²ΡΠΎΠΌΠ°ΡΠΈΠ·ΠΈΡΠΎΠ²Π°Π½Π½ΠΎΠ³ΠΎ ΠΏΡΠΎΠ΅ΠΊΡΠΈΡΠΎΠ²Π°Π½ΠΈΡ Siemens NX. Π§ΡΠΎ ΠΏΠΎΠ·Π²ΠΎΠ»ΡΠ΅Ρ ΡΠΎΠΊΡΠ°ΡΠΈΡΡ Π²ΡΠ΅ΠΌΡ Π½Π° ΠΏΡΠΎΠ΅ΠΊΡΠΈΡΠΎΠ²Π°Π½ΠΈΠ΅ ΠΈ ΠΈΡΠΏΠΎΠ»ΡΠ·ΠΎΠ²Π°ΡΡ Π΅Π³ΠΎ Π² ΠΊΠ°ΡΠ΅ΡΡΠ²Π΅ ΡΡΠ°Π»ΠΎΠ½Π° Π΄Π»Ρ ΡΠ°ΡΡΠ΅ΡΠ° ΠΈ ΠΏΠΎΡΠ»Π΅Π΄ΡΡΡΠ΅Π³ΠΎ ΠΈΠ·ΠΌΠ΅Π½Π΅Π½ΠΈΠ΅ ΠΏΡΠΎΡΡΠΎ Π·Π½Π°ΡΠ΅Π½ΠΈΠΉ Π΄Π»Ρ ΠΏΠΎΠ»ΡΡΠ΅Π½ΠΈΡ Π΄ΡΡΠ³ΠΎΠΉ ΡΠ°Π·ΠΌΠ΅ΡΠ½ΠΎΡΡΠΈ ΡΡΡΠΈΠ½Π³Π΅ΡΠΎΠ²
ΠΠΎΠ΄Ρ ΠΎΠ΄ ΠΊ ΡΠΏΡΠ°Π²Π»Π΅Π½ΠΈΡ Π±Π°Π·ΠΎΠ²ΠΎΠΉ Π³Π΅ΠΎΠΌΠ΅ΡΡΠΈΡΠ΅ΡΠΊΠΎΠΉ ΡΠ΅ΠΎΡΠ΅ΡΠΈΡΠ΅ΡΠΊΠΎΠΉ ΠΈΠ½ΡΠΎΡΠΌΠ°ΡΠΈΠ΅ΠΉ ΡΡΠ·Π΅Π»ΡΠΆΠ° ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ° Π² ΠΊΠΎΠ½ΡΠ΅ΠΊΡΡΠ΅ PLM-ΡΠ΅Ρ Π½ΠΎΠ»ΠΎΠ³ΠΈΠΉ
Π‘ΡΠ°ΡΡΡ ΠΏΡΠΈΡΠ²ΡΡΠ΅Π½Π° Π΄ΠΎΡΠ»ΡΠ΄ΠΆΠ΅Π½Π½Ρ ΠΏΡΠΎΡΠ΅ΡΡΠ² Π·Π°Π±Π΅Π·ΠΏΠ΅ΡΠ΅Π½Π½Ρ ΠΏΡΠΎΠ΅ΠΊΡΡΠ²Π°Π½Π½Ρ ΡΠ° Π²ΠΈΠ³ΠΎΡΠΎΠ²Π»Π΅Π½Π½Ρ Π»ΡΡΠ°ΠΊΠ° Π±Π°Π·ΠΎΠ²ΠΎΡ Π³Π΅ΠΎΠΌΠ΅ΡΡΠΈΡΠ½ΠΎΡ ΡΠ΅ΠΎΡΠ΅ΡΠΈΡΠ½ΠΎΡ ΡΠ½ΡΠΎΡΠΌΠ°ΡΡΡΡ Π² ΡΠΌΠΎΠ²Π°Ρ
Π²ΠΏΡΠΎΠ²Π°Π΄ΠΆΠ΅Π½Π½Ρ Π½ΠΎΠ²ΡΡΠ½ΡΡ
ΡΠ½ΡΠΎΡΠΌΠ°ΡΡΠΉΠ½ΠΈΡ
ΡΠ΅Ρ
Π½ΠΎΠ»ΠΎΠ³ΡΠΉ. Π ΡΡΠ°ΡΡΡ ΠΎΠΏΠΈΡΠ°Π½ΠΎ ΠΊΠΎΠ½ΡΠ΅ΠΏΡΡΡ Π·Π°Π±Π΅Π·ΠΏΠ΅ΡΠ΅Π½Π½Ρ ΠΏΡΠΎΡΠ΅ΡΡ ΠΏΡΠΎΠ΅ΠΊΡΡΠ²Π°Π½Π½Ρ ΡΡΠ·Π΅Π»ΡΠΆΡ Π»ΡΡΠ°ΠΊΠ° Π±Π°Π·ΠΎΠ²ΠΎΡ Π³Π΅ΠΎΠΌΠ΅ΡΡΠΈΡΠ½ΠΎΡ ΡΠ΅ΠΎΡΠ΅ΡΠΈΡΠ½ΠΎΡ ΡΠ½ΡΠΎΡΠΌΠ°ΡΡΡΡ ΠΏΡΠΎΡΡΠ³ΠΎΠΌ Π²ΡΡΠΎΠ³ΠΎ ΠΆΠΈΡΡΡΠ²ΠΎΠ³ΠΎ ΡΠΈΠΊΠ»Ρ Π²ΠΈΡΠΎΠ±Ρ.The article is devoted to research ways of approach to supply designing and manufacturing an aircraft basic geometrical theoretical information in conditions of implementation newest IT. Due to the absence of methodic recommendations to control basic geometrical theoretical information of fuselage of the aircraft in context of PLM technology, in this article is described a conception of supplying designing and manufacturing of fuselage of the aircraft basic geometrical theoretical information during the product lifecycle management. In this article are enlightened important scientific and practical results. The block diagram of information flows is designed during the process of creation a geometrical model of aircraft which provides the mast earlier accessing specialists of different area to the process of concurrent designing. It is proposed the scheme of the product lifecycle management of aircraft which express the way of approach to control basic geometrical theoretical information of fuselage of the aircraft. Also it is introduced the realization of proposed way of approach in context of PLM technology in software ENOVIA V5.Π‘ΡΠ°ΡΡΡ ΠΏΠΎΡΠ²ΡΡΠ΅Π½Π° ΠΈΡΡΠ»Π΅Π΄ΠΎΠ²Π°Π½ΠΈΡ ΠΏΡΠΎΡΠ΅ΡΡΠΎΠ² ΠΎΠ±Π΅ΡΠΏΠ΅ΡΠ΅Π½ΠΈΡ ΠΏΡΠΎΠ΅ΠΊΡΠΈΡΠΎΠ²Π°Π½ΠΈΡ ΠΈ ΠΈΠ·Π³ΠΎΡΠΎΠ²Π»Π΅Π½ΠΈΡ ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ° Π±Π°Π·ΠΎΠ²ΠΎΠΉ Π³Π΅ΠΎΠΌΠ΅ΡΡΠΈΡΠ΅ΡΠΊΠΎΠΉ ΡΠ΅ΠΎΡΠ΅ΡΠΈΡΠ΅ΡΠΊΠΎΠΉ ΠΈΠ½ΡΠΎΡΠΌΠ°ΡΠΈΠ΅ΠΉ Π² ΡΡΠ»ΠΎΠ²ΠΈΡΡ
Π²Π½Π΅Π΄ΡΠ΅Π½ΠΈΡ Π½ΠΎΠ²Π΅ΠΉΡΠΈΡ
ΠΈΠ½ΡΠΎΡΠΌΠ°ΡΠΈΠΎΠ½Π½ΡΡ
ΡΠ΅Ρ
Π½ΠΎΠ»ΠΎΠ³ΠΈΠΉ. Π ΡΡΠ°ΡΡΠ΅ ΠΎΠΏΠΈΡΠ°Π½ΠΎ ΠΊΠΎΠ½ΡΠ΅ΠΏΡΠΈΡ ΠΎΠ±Π΅ΡΠΏΠ΅ΡΠ΅Π½ΠΈΡ ΠΏΡΠΎΡΠ΅ΡΡΠ° ΠΏΡΠΎΠ΅ΠΊΡΠΈΡΠΎΠ²Π°Π½ΠΈΡ ΡΡΠ·Π΅Π»ΡΠΆΠ° ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ° Π±Π°Π·ΠΎΠ²ΠΎΠΉ Π³Π΅ΠΎΠΌΠ΅ΡΡΠΈΡΠ΅ΡΠΊΠΎΠΉ ΡΠ΅ΠΎΡΠ΅ΡΠΈΡΠ΅ΡΠΊΠΎΠΉ ΠΈΠ½ΡΠΎΡΠΌΠ°ΡΠΈΠ΅ΠΉ Π½Π° ΠΏΡΠΎΡΡΠΆΠ΅Π½ΠΈΠΈ Π²ΡΠ΅Π³ΠΎ ΠΆΠΈΠ·Π½Π΅Π½Π½ΠΎΠ³ΠΎ ΡΠΈΠΊΠ»Π° ΠΈΠ·Π΄Π΅Π»ΠΈΡ
ΠΠΎΠΌΠΏΡΡΡΠ΅ΡΠ½ΡΠ΅ ΡΡΡΡΠΊΡΡΡΠ½ΠΎ-ΠΏΠ°ΡΠ°ΠΌΠ΅ΡΡΠΈΡΠ΅ΡΠΊΠΈΠ΅ Π³Π΅ΠΎΠΌΠ΅ΡΡΠΈΡΠ΅ΡΠΊΠΈΠ΅ ΠΌΠΎΠ΄Π΅Π»ΠΈ ΠΊΠ°ΠΊ ΡΡΠ΅Π΄ΡΡΠ²Π° ΠΊΠΎΠ½ΡΡΡΡΠΊΡΠΎΡΡΠΊΠΎ-ΡΠ΅Ρ Π½ΠΎΠ»ΠΎΠ³ΠΈΡΠ΅ΡΠΊΠΎΠΉ ΠΎΠΏΡΠΈΠΌΠΈΠ·Π°ΡΠΈΠΈ ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ°
ΠΡΠΎΠ°Π½Π°Π»ΡΠ·ΠΎΠ²Π°Π½ΠΎ ΠΏΠΈΡΠ°Π½Π½Ρ Π΅ΡΠ΅ΠΊΡΠΈΠ²Π½ΠΎΠ³ΠΎ Π·Π°ΡΡΠΎΡΡΠ²Π°Π½Π½Ρ ΡΡΡΡΠΊΡΡΡΠ½ΠΎ-ΠΏΠ°ΡΠ°ΠΌΠ΅ΡΡΠΈΡΠ½ΠΎΡ ΠΌΠ΅ΡΠΎΠ΄ΠΎΠ»ΠΎΠ³ΡΡ ΡΠΎΡΠΌΠΎΡΡΠ²ΠΎΡΠ΅Π½Π½Ρ Π΄Π»Ρ ΠΏΡΠΎΠ²Π΅Π΄Π΅Π½Π½Ρ ΠΊΠΎΠΌΠΏΠ»Π΅ΠΊΡΠ½ΠΎΡ ΠΎΠΏΡΠΈΠΌΡΠ·Π°ΡΡΡ ΠΏΡΠΎΠΌΠΈΡΠ»ΠΎΠ²ΠΎΡ ΠΏΡΠΎΠ΄ΡΠΊΡΡΡ. ΠΠ° ΠΏΡΠΈΠΊΠ»Π°Π΄Ρ Π²Π°ΡΡΠ°Π½ΡΠ½ΠΎΠ³ΠΎ ΠΊΠΎΠ½ΡΡΡΡΠΊΡΠΎΡΡΡΠΊΠΎ-ΡΠ΅Ρ
Π½ΠΎΠ»ΠΎΠ³ΡΡΠ½ΠΎΠ³ΠΎ ΠΏΡΠΎΠ΅ΠΊΡΡΠ²Π°Π½Π½Ρ Π»ΠΎΠ½ΠΆΠ΅ΡΠΎΠ½Π° ΠΊΡΠΈΠ»Π° ΡΡΡΠ°ΡΠ½ΠΎΠ³ΠΎ Π»ΡΡΠ°ΠΊΠ° ΠΏΠΎΠ΄Π°Π½ΠΎ ΠΎΡΠ½ΠΎΠ²Π½Ρ ΠΏΡΠΈΠΉΠΎΠΌΠΈ ΡΠΎΠ·ΡΠΎΠ±Π»Π΅Π½ΠΎΡ ΠΌΠ΅ΡΠΎΠ΄ΠΈΠΊΠΈ. ΠΠΊΡΠ΅Π½ΡΠΎΠ²Π°Π½ΠΎ ΡΠ²Π°Π³Ρ Π½Π° ΡΡ
ΡΠ½ΡΠ²Π΅ΡΡΠ°Π»ΡΠ½ΠΎΠΌΡ ΡΠ° ΡΠ½Π²Π°ΡΡΠ°Π½ΡΠ½ΠΎΠΌΡ Ρ
Π°ΡΠ°ΠΊΡΠ΅ΡΡ ΡΠΎΠ΄ΠΎ ΡΡΠ·Π½ΠΎΠΌΠ°Π½ΡΡΠ½ΠΈΡ
ΠΎΠΏΡΠ°ΡΡΠΎΠ²ΡΠ²Π°Π½ΠΈΡ
ΠΎΠ±βΡΠΊΡΡΠ² Ρ ΠΏΡΠΎΡΠ΅ΡΡΠ². ΠΠΊΡΠ΅ΡΠ»Π΅Π½ΠΎ ΠΏΠ΅ΡΡΠΏΠ΅ΠΊΡΠΈΠ²ΠΈ ΠΏΠΎΠ΄Π°Π»ΡΡΠΎΠ³ΠΎ ΡΠΎΠ·Π²ΠΈΡΠΊΡ ΡΠΎΠ·Π³Π»ΡΠ½ΡΡΠΎΠ³ΠΎ Π½Π°ΠΏΡΡΠΌΠΊΡ Π½Π°ΡΠΊΠΎΠ²ΠΈΡ
Π΄ΠΎΡΠ»ΡΠ΄ΠΆΠ΅Π½Ρ ΡΡΠΎΡΠΎΠ²Π½ΠΎ ΠΏΠΎΡΠΈΡΠ΅Π½Π½Ρ ΠΏΡΠ°ΠΊΡΠΈΡΠ½ΠΎΠ³ΠΎ Π²ΠΈΠΊΠΎΡΠΈΡΡΠ°Π½Π½Ρ ΡΡ
ΡΠ΅Π·ΡΠ»ΡΡΠ°ΡΡΠ² ΠΏΡΠ΄ ΡΠ°Ρ ΠΊΠΎΠΌΠΏβΡΡΠ΅ΡΠ½ΠΎΠ³ΠΎ ΠΌΠΎΠ΄Π΅Π»ΡΠ²Π°Π½Π½Ρ ΡΠ½ΡΠΈΡ
Π²ΠΈΡΠΎΠ±ΡΠ² ΠΌΠ°ΡΠΈΠ½ΠΎΠ±ΡΠ΄ΡΠ²Π°Π½Π½Ρ.The current stage of technical progress is characterized by the extensive use of computer information technology in the creation of various industrial products. Therefore, the development and introduction of new effective methods, techniques and algorithms for computer-aided design are relevant today. It is known that the system consisting of the optimal elements itself is not necessarily the same. Therefore, complex optimization is very important for the designed technical objects. Geometric models have a special place in integrating for computational models of technical objects because significant number of output characteristics substantially depend on geometrical parameters. The applications of structural-parametric geometric modeling methodology for design-technologic optimization of technical products are analyzed in this article. Variant engineering design was shown on the example of spar of airplane wing. Basic techniques of proposed method were presented. The emphasis was placed on their universal and invariant character for different objects and processes. Prospects for further development of this scientific field studies on the spread of its practical application to optimal designing of different industrial products were considered. The main advantages of the analyzed computer-integrated engineering and process design of industrial products based on the use of structural-parametric geometric models is the universality and invariance of the proposed techniques for different objects and processes. Featured approach provides a flexible and productive implementation of complex optimization of industrial products. This direction of creation of technical products requires further intensive research for its successful practical realization.ΠΡΠΎΠ°Π½Π°Π»ΠΈΠ·ΠΈΡΠΎΠ²Π°Π½Ρ Π²ΠΎΠΏΡΠΎΡΡ ΡΡΡΠ΅ΠΊΡΠΈΠ²Π½ΠΎΠ³ΠΎ ΠΏΡΠΈΠΌΠ΅Π½Π΅Π½ΠΈΡ ΡΡΡΡΠΊΡΡΡΠ½ΠΎ-ΠΏΠ°ΡΠ°ΠΌΠ΅ΡΡΠΈΡΠ΅ΡΠΊΠΎΠΉ ΠΌΠ΅ΡΠΎΠ΄ΠΎΠ»ΠΎΠ³ΠΈΠΈ ΡΠΎΡΠΌΠΎΠΎΠ±ΡΠ°Π·ΠΎΠ²Π°Π½ΠΈΡ Π΄Π»Ρ ΠΏΡΠΎΠ²Π΅Π΄Π΅Π½ΠΈΡ ΠΊΠΎΠΌΠΏΠ»Π΅ΠΊΡΠ½ΠΎΠΉ ΠΎΠΏΡΠΈΠΌΠΈΠ·Π°ΡΠΈΠΈ ΠΏΡΠΎΠΌΡΡΠ»Π΅Π½Π½ΠΎΠΉ ΠΏΡΠΎΠ΄ΡΠΊΡΠΈΠΈ. ΠΠ° ΠΏΡΠΈΠΌΠ΅ΡΠ΅ Π²Π°ΡΠΈΠ°Π½ΡΠ½ΠΎΠ³ΠΎ ΠΊΠΎΠ½ΡΡΡΡΠΊΡΠΎΡΡΠΊΠΎ-ΡΠ΅Ρ
Π½ΠΎΠ»ΠΎΠ³ΠΈΡΠ΅ΡΠΊΠΎΠ³ΠΎ ΠΏΡΠΎΠ΅ΠΊΡΠΈΡΠΎΠ²Π°Π½ΠΈΡ Π»ΠΎΠ½ΠΆΠ΅ΡΠΎΠ½Π° ΠΊΡΡΠ»Π° ΡΠΎΠ²ΡΠ΅ΠΌΠ΅Π½Π½ΠΎΠ³ΠΎ ΡΠ°ΠΌΠΎΠ»Π΅ΡΠ° ΠΏΡΠ΅Π΄ΡΡΠ°Π²Π»Π΅Π½Ρ ΠΎΡΠ½ΠΎΠ²Π½ΡΠ΅ ΠΏΡΠΈΠ΅ΠΌΡ ΡΠ°Π·ΡΠ°Π±ΠΎΡΠ°Π½Π½ΠΎΠΉ ΠΌΠ΅ΡΠΎΠ΄ΠΈΠΊΠΈ. ΠΠΊΡΠ΅Π½ΡΠΈΡΠΎΠ²Π°Π½ΠΎ Π²Π½ΠΈΠΌΠ°Π½ΠΈΠ΅ Π½Π° ΠΈΡ
ΡΠ½ΠΈΠ²Π΅ΡΡΠ°Π»ΡΠ½ΠΎΠΌ ΠΈ ΠΈΠ½Π²Π°ΡΠΈΠ°Π½ΡΠ½ΠΎΠΌ Ρ
Π°ΡΠ°ΠΊΡΠ΅ΡΠ΅ ΠΏΠΎ ΠΎΡΠ½ΠΎΡΠ΅Π½ΠΈΡ ΠΊ ΡΠ°Π·Π½ΠΎΠΎΠ±ΡΠ°Π·Π½ΡΠΌ ΠΎΠ±ΡΠ΅ΠΊΡΠ°ΠΌ ΠΈ ΠΏΡΠΎΡΠ΅ΡΡΠ°ΠΌ. ΠΠΏΡΠ΅Π΄Π΅Π»Π΅Π½Ρ ΠΏΠ΅ΡΡΠΏΠ΅ΠΊΡΠΈΠ²Ρ Π΄Π°Π»ΡΠ½Π΅ΠΉΡΠ΅Π³ΠΎ ΡΠ°Π·Π²ΠΈΡΠΈΡ ΡΠ°ΡΡΠΌΠΎΡΡΠ΅Π½Π½ΠΎΠ³ΠΎ Π½Π°ΠΏΡΠ°Π²Π»Π΅Π½ΠΈΡ Π½Π°ΡΡΠ½ΡΡ
ΠΈΡΡΠ»Π΅Π΄ΠΎΠ²Π°Π½ΠΈΠΉ ΠΏΠΎ ΠΏΡΠ°ΠΊΡΠΈΡΠ΅ΡΠΊΠΎΠΌΡ ΠΈΡΠΏΠΎΠ»ΡΠ·ΠΎΠ²Π°Π½ΠΈΡ ΠΈΡ
ΡΠ΅Π·ΡΠ»ΡΡΠ°ΡΠΎΠ² ΠΏΡΠΈ ΠΊΠΎΠΌΠΏΡΡΡΠ΅ΡΠ½ΠΎΠΌ ΠΌΠΎΠ΄Π΅Π»ΠΈΡΠΎΠ²Π°Π½ΠΈΠΈ Π΄ΡΡΠ³ΠΈΡ
ΠΈΠ·Π΄Π΅Π»ΠΈΠΉ ΠΌΠ°ΡΠΈΠ½ΠΎΡΡΡΠΎΠ΅Π½ΠΈΡ
New national and regional bryophyte records, 49
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Metalloproteinases and their inhibitorsβdiagnostic and therapeutic opportunities in orthopedics
Matrix metalloproteinases (MMPs) and related enzymes (ADAMs, ADAMTS) and their inhibitors control matrix turnover and function. Recent advances in our understanding of musculoskeletal conditions such as tendinopathy, arthritis, Dupuytren's disease, degenerative disc disease, and bone and soft tissue healing suggest that MMPs have prominant roles. Importantly, MMPs are amenable to inhibition by cheap, safe, and widely available drugs such as the tetracycline antibiotics and the bisphosphonates. This indicates that these MMP inhibitors, if proven effective for any novel indication, may be quickly brought into clinical practice
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