методика количественной оценки технологичности конструкции

Àâèàöèîííàÿ òåõíèêà
Aircraft Engineering
ÓÄÊ 658.512; 004.942
ÌÅÒÎÄÈÊÀ ÊÎËÈ×ÅÑÒÂÅÍÍÎÉ ÎÖÅÍÊÈ ÒÅÕÍÎËÎÃÈ×ÍÎÑÒÈ
ÊÎÍÑÒÐÓÊÖÈÈ ÈÇÄÅËÈÉ ÀÂÈÀÖÈÎÍÍÎÉ ÒÅÕÍÈÊÈ
Ãîâîðêîâ À.Ñ.
Èðêóòñêèé ãîñóäàðñòâåííûé òåõíè÷åñêèé óíèâåðñèòåò (íàöèîíàëüíûé èññëåäîâàòåëüñêèé óíèâåðñèòåò),
óë. Ëåðìîíòîâà, 83, Èðêóòñê, 664074, Ðîññèÿ
e-mail: [email protected]
Ðàññìîòðåíà ìåòîäèêà êîëè÷åñòâåííîé îöåíêè òåõíîëîãè÷íîñòè êîíñòðóêöèè äåòàëè ïëàíåðà íà îñíîâå âçàèìîäåéñòâèÿ îòäåëüíûõ ÷àñòíûõ ïîêàçàòåëåé ñ ó÷åòîì âåñîâûõ êîýôôèöèåíòîâ. Ïðåäëîæåí àëãîðèòì ïðîâåäåíèÿ
òåõíîëîãè÷åñêîãî êîíòðîëÿ äåòàëè íà îñíîâå å¸ òðåõìåðíîé ìîäåëè.
Êëþ÷åâûå ñëîâà: äåòàëü ïëàíåðà, ìîäåëü, òåõíîëîãè÷íîñòü, êîíñòðóêòèâíûé ýëåìåíò, ÷àñòíûé ïîêàçàòåëü òåõíîëîãè÷íîñòè.
Ìíîãîîáðàçèå òåõíè÷åñêîé ëèòåðàòóðû, ðåêîìåíäàöèè ñïðàâî÷íèêîâ ïî òåõíîëîãè÷íîñòè êîíñòðóêöèè èçäåëèé (ÒÊÈ) ìàøèíîñòðîåíèÿ [1, 3]
îòðàæàþò îñíîâíûå ñâåäåíèÿ î ÒÊÈ, ñîñòàâå è
îñîáåííîñòÿõ ÷àñòíûõ ïîêàçàòåëåé, ìåòîäè÷åñêèå
îñíîâû å¸ îáåñïå÷åíèÿ è îöåíêè.
Ïðè ðàçðàáîòêå äåòàëè â CAD/CAM/CAE/
/PDM-ñèñòåìàõ ðàöèîíàëüíûì ðåøåíèåì ÿâëÿåòñÿ ïðîâåäåíèå îöåíêè êîíñòðóêöèè íà òåõíîëîãè÷íîñòü óæå íà íà÷àëüíûõ ýòàïàõ çàïóñêà ïðîäóêöèè.
Äëÿ ñíèæåíèÿ öèêëà ïîäãîòîâêè äîêóìåíòàöèè è
çàïóñêà â ïðîèçâîäñòâî ïåðåä êîíñòðóêòîðîì è òåõíîëîãîì ñòàâÿòñÿ ñëåäóþùèå çàäà÷è:
— âûáîð ñîâðåìåííûõ êîíñòðóêòèâíûõ ðåøåíèé, îïòèìàëüíîãî âàðèàíòà èçãîòîâëåíèÿ è êîíñòðóêòèâíîé êîìïîíîâêè äåòàëè;
— ðàöèîíàëüíûé âûáîð êîíñòðóêöèè äåòàëè â
çàâèñèìîñòè îò ôóíêöèîíàëüíîñòè äåòàëè (âûïîëíÿåìîé ôóíêöèè);
— èñïîëüçîâàíèå ñòàíäàðòíûõ, áèáëèîòå÷íûõ
êîíñòðóêòèâíûõ ýëåìåíòîâ (ÊÝ) ïðè ìîäåëèðîâàíèè äåòàëåé ïëàíåðà (íàïðèìåð, â ñèñòåìå NX);
— âîçìîæíîñòü ïðèìåíåíèÿ òèïîâûõ òåõíîëîãè÷åñêèõ ïðîöåññîâ èçãîòîâëåíèÿ äåòàëåé;
— ñíèæåíèå òðóäîåìêîñòè èçãîòîâëåíèÿ äåòàëåé.
Îáðàáàòûâàÿ êîíñòðóêöèþ äåòàëè ïëàíåðà íà
ïðîèçâîäñòâåííóþ òåõíîëîãè÷íîñòü, íóæíî ó÷èòûâàòü ìàñøòàáû âûïóñêà, òèï ïðîèçâîäñòâà è ñïåöèôèêó çàâîäà-èçãîòîâèòåëÿ, ñ òåì ÷òîáû êîíñòðóê-
öèè îòäåëüíûõ äåòàëåé ìîãëè áûòü èçãîòîâëåíû ñ
ó÷åòîì óêàçàííûõ ôàêòîðîâ.
Íà ðàííèõ ñòàäèÿõ òåõíîëîãè÷åñêîé ïîäãîòîâêè ïðîèçâîäñòâà îöåíêà óðîâíÿ òåõíîëîãè÷íîñòè ïî
îñíîâíûì ïîêàçàòåëÿì ñòàíäàðòà [2, 4] çàòðóäíèòåëüíà, à ÷àñòî è íåâîçìîæíà â ïîëíîì îáúåìå ââèäó íåïîëíîòû èíôîðìàöèè (íîðì âðåìåíè, ïåðå÷åíü îáîðóäîâàíèÿ è äð.). Äëÿ îáåñïå÷åíèÿ ïðîèçâîäñòâåííîé òåõíîëîãè÷íîñòè êîíñòðóêöèè êà÷åñòâåííóþ îöåíêó ìîæíî ïðîâåñòè ïî ñâîéñòâàì
ÒÊÈ, à êîëè÷åñòâåííóþ — ñ ïîìîùüþ ÷àñòíûõ ïîêàçàòåëåé.
Îêîí÷àòåëüíàÿ îöåíêà ïðîèçâîäñòâåííîé òåõíîëîãè÷íîñòè â óñëîâèÿõ îïûòíîãî ïðîèçâîäñòâà äåòàëåé ïëàíåðà áûëà âûïîëíåíà ïî ÷àñòíûì ïîêàçàòåëÿì ïóòåì ñðàâíåíèÿ âàðèàíòîâ ïðåäëàãàåìîé
äåòàëè ñ àíàëîãîì, ñóùåñòâóþùèì íà ïðåäïðèÿòèè.
Ïðè îòñóòñòâèè àíàëîãà îïðåäåëÿþò êîìïëåêñíûé
ïîêàçàòåëü, êîòîðûé äîëæåí áûòü áîëüøå 0,5. Âåëè÷èíà êîìïëåêñíîãî ïîêàçàòåëÿ îïðåäåëÿåòñÿ èç
óñëîâèé êðàéíå íåáëàãîïðèÿòíîãî ñî÷åòàíèÿ ïîêàçàòåëåé íà îñíîâå ýêñïåðòíûõ îöåíîê.
 äàííîé ðàáîòå ðàññìàòðèâàåòñÿ ìåòîäèêà ïî
ðàñ÷åòó òåõíîëîãè÷íîñòè è îöåíêå êà÷åñòâà îáúåêòà,
ïîçâîëÿþùàÿ ôîðìàëèçîâàòü ïðîöåññ îöåíêè äåòàëè ïëàíåðà íà òåõíîëîãè÷íîñòü è èçìåíÿòü õàðàêòåðèñòèêè è ïàðàìåòðû ÷àñòíûõ ïîêàçàòåëåé.
Èñõîäíûå äàííûå äëÿ ðàñ÷åòà òåõíîëîãè÷íîñòè êîíñòðóêöèè äåòàëè íà ïðèìåðå äèàôðàãìû (ñì.
ðèñóíîê) ïðèâåäåíû â òàáë. 1.
ÂÅÑÒÍÈÊ ÌÀÈ. Ò.20. ¹1
!
Àâèàöèîííàÿ òåõíèêà
Aircraft Engineering
íèÿ âàðèàíòîâ òåõíîëîãèè îñóùåñòâëåíà ñ ïîìîùüþ
êîìïëåêñíîãî ïîêàçàòåëÿ (òàáë. 2), [2]
n
p=
∑ ki ϕi
i =1
n
∑ ϕi
,
(1)
i =1
ãäå ki — çíà÷åíèå i-ãî ÷àñòíîãî ïîêàçàòåëÿ òåõíîëîãè÷íîñòè äåòàëè;
Äèàôðàãìà òîðìîçíîãî ùèòêà ñàìîë¸òà
Êîëè÷åñòâåííàÿ îöåíêà òåõíîëîãè÷íîñòè äåòàëè «äèàôðàãìà» íà ýòàïå ïðîåêòèðîâàíèÿ è ñðàâíå-
ϕi — êîýôôèöèåíò âåñîìîñòè i-ãî ÷àñòíîãî ïîêàçàòåëÿ òåõíîëîãè÷íîñòè äåòàëè;
n — êîëè÷åñòâî ïðèíÿòûõ ïîêàçàòåëåé, îïðåäåëÿåìûõ ýêñïåðòîì, äîëæíî áûòü íå ìåíåå 5.
Òàáëèöà 1
Èñõîäíûå äàííûå äëÿ ðàñ÷åòà òåõíîëîãè÷íîñòè êîíñòðóêöèè äèàôðàãìû òîðìîçíîãî ùèòêà ñàìîëåòà
¹
Íàèìåíîâàíèå äàííûõ
1
Äàííûå ïî ãåîìåòðè÷åñêèì ïàðàìåòðàì
2
Îáúåì âûïóñêà â ãîä
3
Ìàññà äåòàëè
4
Êîëè÷åñòâî íàèìåíîâàíèé êîíñòðóêòèâíûõ ýëåìåíòîâ
5
Âûõîä íà òåîðåòè÷åñêèé êîíòóð
6
Ìàòåðèàë
7
Äîïóñê íà àýðîäèíàìè÷åñêèé êîíòóð
Çíà÷åíèå
Ìîäåëü äåòàëè, òåõíè÷åñêèå óñëîâèÿ
0-100 øò.
Íå áîëåå 0,100 êã
Áîëåå 3
Äà
Ä16ÀÒ
±1,0
Òàáëèöà 2
Ñâîäíàÿ âåäîìîñòü ðàñ÷åòà ïîêàçàòåëåé òåõíîëîãè÷íîñòè äåòàëè ÀÒ
¹
Íàèìåíîâàíèå ÷àñòíîãî ïîêàçàòåëÿ òåõíîëîãè÷íîñòè
Êîýôôèöèåíò
âåñîìîñòè, ϕi
ki ϕi
1
Îáúåì âûïóñêà â ãîä, kãîä
0,30
0,06
0,018
2
Òåõíîëîãè÷íîñòü ðàçäåëèòåëüíîé îïåðàöèè, kðàç
1,00
0,12
0,12
3
Òåõíîëîãè÷íîñòü ôîðìîèçìåíÿþùåé îïåðàöèè, kôîð
0,90
0,13
0,117
4
Óðîâåíü ïîâòîðÿåìîñòè ÊÝ, âõîäÿùèõ â èçäåëèå, kýë
0,90
0,12
0,108
5
Ìàññà äåòàëè, kì
1,00
0,07
0,07
6
Ãàáàðèòíûå ðàçìåðû, kðàç
0,80
0,08
0,064
7
Ôîðìà îáâîäîâ, kô.îá
0,75
0,06
0,045
8
Ôîðìà êîíòóðà, kô.êîí
0,60
0,05
0,03
9
Óðîâåíü êðèâèçíû, kóð.êð
0,9
0,11
0,099
10
Äîïóñê íà àýðîäèíàìè÷åñêèé êîíòóð, kàýð
0,40
0,05
0,02
11
Âûõîä íà îáâîä, kÒÊ
0,5
0,08
0,04
12
Ðàñïîëîæåíèå ýëåìåíòîâ îòíîñèòåëüíî óñëîâíîé
ïëîñêîñòè äåòàëè, kN
0,8
0,07
0,056
1,00
0,787
Èòîãî
!
Çíà÷åíèå
ïîêàçàòåëÿ
ÂÅÑÒÍÈÊ ÌÀÈ. Ò.20. ¹1
Àâèàöèîííàÿ òåõíèêà
Aircraft Engineering
Äàëåå âåëè÷èíû ïîêàçàòåëåé óðîâíÿ òåõíîëîãè÷íîñòè ïîêàçàòåëåé â äàííîé ðàáîòå ïðèíÿòû
óñëîâíûìè.
Ïîêàçàòåëè îáúåìà âûïóñêà â ãîä kãîä (òàáë. 3)
îöåíèâàþò âîçìîæíîñòü ìåõàíèçàöèè è àâòîìàòèçàöèè ïðîöåññà èçãîòîâëåíèÿ äåòàëè. ×åì áîëüøå
îáúåì âûïóñêà, òåì ýôôåêòèâíåå ïðèìåíåíèå
ñðåäñòâ ìåõàíèçàöèè è àâòîìàòèçàöèè è, ñîîòâåòñòâåííî, ñóùåñòâåííåå ñíèæåíèå òðóäîåìêîñòè è
ñåáåñòîèìîñòè äåòàëè.
Ïîêàçàòåëü òåõíîëîãè÷íîñòè â çàâèñèìîñòè îò
âèäà ðàçäåëèòåëüíîé kðàç îïåðàöèè ïðè èçãîòîâëåíèè çàãîòîâêè äåòàëè èç ëèñòà (òàáë. 4) ó÷èòûâàåò
òàêîé ïîêàçàòåëü ÒÊÈ, êàê òåõíîëîãè÷åñêàÿ ñåáåñòîèìîñòü çàãîòîâêè.
Ïîêàçàòåëü òåõíîëîãè÷íîñòè â çàâèñèìîñòè îò
âèäà ôîðìîîáðàçóþùåé kôîð îïåðàöèè ïðè èçãîòîâëåíèè ôîðìû äåòàëè èç ëèñòà (òàáë. 5) ó÷èòûâàåò
òàêîé ïîêàçàòåëü ÒÊÈ, êàê òåõíîëîãè÷åñêàÿ ñåáåñòîèìîñòü çàãîòîâêè, òåõíîëîãè÷åñêàÿ ïðîñòîòà.
Òàáëèöà 3
Îáúåì âûïóñêà äåòàëåé ïëàíåðà â ãîä
¹
Îáúåì âûïóñêà
äåòàëåé ïëàíåðà â ãîä
kãîä
1
1-10
0,1
2
10-50
0,2
3
50-100
0,3
4
100-200
0,4
5
200-300
0,5
6
300-400
0,6
7
400-600
0,7
8
600-800
0,8
9
800-1000
0,9
10
1000 è âûøå
1,0
Òàáëèöà 4
Ïîêàçàòåëü òåõíîëîãè÷íîñòè â çàâèñèìîñòè
îò âèäà ðàçäåëèòåëüíîé îïåðàöèè
¹
Òåõíîëîãè÷íîñòü ðàçäåëèòåëüíîé
îïåðàöèè
kðàç
1
Íà ôðåçåðíîì ñòàíêå ñ ×ÏÓ
1,0
2
Íà ôðåçåðíîì ñòàíêå ïî øàáëîíó
0,8
3
 øòàìïå
0,6
4
Ãèëüîòèííûå íîæíèöû
0,4
5
Ðîëèêîâûå íîæíèöû
0,2
Òàáëèöà 5
Ïîêàçàòåëü òåõíîëîãè÷íîñòè â çàâèñèìîñòè
îò âèäà ôîðìîîáðàçóþùåé îïåðàöèè
¹
Òåõíîëîãè÷íîñòü
ôîðìîîáðàçóþùåé îïåðàöèè
kôîð
1
Ôîðìîâêà ýëàñòè÷íîé ñðåäîé
1,0
2
Ôîðìîâêà íà ïàäàþùèõ ìîëîòàõ
0,8
3
Ãèáêà â øòàìïå
0,6
4
Îáòÿæêà
0,3
Ïðè íåñêîëüêèõ âèäàõ îïåðàöèé ôîðìîîáðàçîâàíèÿ îäíîé äåòàëè îïðåäåëÿþò ñðåäíåâçâåøåííîå
çíà÷åíèå ïîêàçàòåëÿ ïî ôîðìóëå
n
kôîð
ñð
=
∑ kôîð i pi
i =1
p
,
(2)
ãäå ð — îáùåå êîëè÷åñòâî ïðèìåíÿåìûõ ôîðìîîáðàçóþùèõ îïåðàöèé ïðè èçãîòîâëåíèè äåòàëè;
kôîð i — çíà÷åíèå ïàðàìåòðà òåõíîëîãè÷íîñòè ïî
i-ìó ïàðàìåòðó;
pi — êîëè÷åñòâî îïåðàöèé i-ãî âèäà.
Ïîêàçàòåëü kýë, õàðàêòåðèçóþùèé ïîâòîðÿåìîñòü êîíñòðóêòèâíûõ ýëåìåíòîâ, âõîäÿùèõ â êîíñòðóêöèþ äåòàëè, âûáèðàåòñÿ èç òàáë. 6.
Ïðè êîëè÷åñòâå êîíñòðóêòèâíûõ ýëåìåíòîâ
áîëåå 40 îöåíêà ïîêàçàòåëÿ ïðèíèìàåòñÿ â çàâèñèìîñòè îò ñëîæíîñòè ôîðìîîáðàçóþùåé îïåðàöèè â
ïðåäåëàõ 0,40—0,10.
Ïîêàçàòåëü kì, çàâèñÿùèé îò ìàññû äåòàëè, îïðåäåëÿåòñÿ ïî òàáë. 7 è ó÷èòûâàåò ñâîéñòâî ÒÊÈ.
Äàííûå â òàáëèöå ïðèìåíèìû òîëüêî äëÿ äåòàëåé
ïëàíåðà ñàìîëåòà.
Ïîêàçàòåëü kðàç, õàðàêòåðèçóþùèé ãàáàðèòíûå
ðàçìåðû äåòàëè, âûáèðàåòñÿ ïî òàáë. 8.
Ïîêàçàòåëü kô.îá, ó÷èòûâàþùèé ôîðìó îáâîäîâ,
îïðåäåëÿåòñÿ èç öåëåâîãî íàçíà÷åíèÿ âñåé äåòàëè
èëè îòäåëüíûõ åå ýëåìåíòîâ. Ïîêàçàòåëè ôîðìû
îáâîäîâ ïðèâåäåíû â òàáë. 9.
Ïîêàçàòåëü kô.êîí, ó÷èòûâàþùèé ôîðìó êîíòóðà, îïðåäåëÿåòñÿ èç êîíñòðóêòèâíîãî ïðåäñòàâëåíèÿ
äåòàëè èëè åå îòäåëüíûõ ýëåìåíòîâ: áîðò, ðåáðî è
äð. Ïîêàçàòåëè ôîðìû êîíòóðîâ ïðèâåäåíû â
òàáë. 10.
Ïîêàçàòåëü kóð.êð, ó÷èòûâàþùèé óðîâåíü êðèâèçíû äåòàëè, îïðåäåëÿåòñÿ èç êîíñòðóêòèâíîãî
ïðåäñòàâëåíèÿ äåòàëè èëè îòäåëüíûõ ýëåìåíòîâ.
Ïîêàçàòåëè óðîâíÿ êðèâèçíû ïðèâåäåíû â òàáë. 11.
ÂÅÑÒÍÈÊ ÌÀÈ. Ò.20. ¹1
!!
Àâèàöèîííàÿ òåõíèêà
Aircraft Engineering
Òàáëèöà 6
Óðîâåíü ïîâòîðÿåìîñòè êîíñòðóêòèâíûõ ýëåìåíòîâ â äåòàëè
¹
Êîëè÷åñòâî íàèìåíîâàíèé ýëåìåíòîâ
Êîëè÷åñòâî ýëåìåíòîâ
kýë
1-2
1-4
1,0
Áîëåå 4
0,95
4-10
0,90
Áîëåå 10
0,85
10-20
0,80
Áîëåå 20
0,75
20-30
0,70
Áîëåå 30
0,60
30-40
0,50
Áîëåå 40
0,40
1
2
3
3-5
4
5
5-8
6
7
8-12
8
9
12-20
10
Òàáëèöà 9
Òàáëèöà 7
Ïîêàçàòåëü ôîðìû îáâîäîâ
Ïîêàçàòåëü ìàññû äåòàëè
¹
Ìàññà äåòàëè, êã
kì
¹
1
0-0,5
1,0
1
Ïëîñêàÿ
1,0
2
0,5-1,0
0,8
2
Öèëèíäðè÷åñêàÿ
0,75
3
1,0-2,0
0,6
3
Êîíè÷åñêàÿ
0,5
4
2,0-5,0
0,4
4
Äâîéíîé êðèâèçíû
0,2
5
5,0-10,0
0,2
6
Áîëåå 10,0
0,1
Ïîêàçàòåëü ôîðìû êîíòóðîâ
Ïîêàçàòåëü òåõíîëîãè÷íîñòè
ãàáàðèòíûõ ðàçìåðîâ äåòàëè
¹
1
Îäíîìåðíàÿ, l/b>5
Äëèíà l: äî 0,5
¹
Ôîðìà êîíòóðîâ
kô.êîí
1
Ïðÿìîëèíåéíàÿ
1,0
2
Äóãè îêðóæíîñòè
0,7
kðàç
3
Êðèâîëèíåéíàÿ
0,6
1
4
Ïðîèçâîëüíàÿ
0,5
2
Äëèíà l:äî 2
0,85
3
Äëèíà l:äî 6
0,75
4
Äëèíà l:ñâûøå 6
0,5
¹
äî 0,5
0,9
1
Ìàëàÿ êðèâèçíà, r>1
0,9
6
äî 2
0,8
2
Áîëüøàÿ êðèâèçíà, r<1
0,6
7
äî 6
0,7
8
ñâûøå 6
0,4
äî 0,5
0,8
10
äî 2
0,7
11
äî 6
0,5
12
ñâûøå 6
0,3
5
9
!"
Òèï äåòàëè
kô.îá
Òàáëèöà 10
Òàáëèöà 8
Ãàáàðèòíûå
ðàçìåðû, ì
Ôîðìà îáâîäîâ
Äâóìåðíàÿ, l/b<5
Òðåõìåðíàÿ
ÂÅÑÒÍÈÊ ÌÀÈ. Ò.20. ¹1
Òàáëèöà 11
Ïîêàçàòåëü óðîâíÿ êðèâèçíû
Óðîâåíü êðèâèçíû
kóð.êð
Ïîêàçàòåëü kàýð, ó÷èòûâàþùèé äîïóñê íà àýðîäèíàìè÷åñêèé êîíòóð, îïðåäåëÿåòñÿ èç öåëåâîé
ôóíêöèè äåòàëè (òàáë. 12).
Ïîêàçàòåëü kÒÊ, ó÷èòûâàþùèé âûõîä ýëåìåíòîâ
äåòàëè íà òåîðåòè÷åñêèé êîíòóð, îïðåäåëÿåòñÿ â
çàâèñèìîñòè îò öåëåâîé ôóíêöèè äåòàëè (òàáë. 13).
Ïîêàçàòåëü kN, ó÷èòûâàþùèé ðàñïîëîæåíèå
êîíñòðóêòèâíûõ ýëåìåíòîâ äåòàëè îòíîñèòåëüíî
óëîâíîé ïëîñêîñòè äåòàëè, îïðåäåëÿåòñÿ ïî òàáë. 14.
Àâèàöèîííàÿ òåõíèêà
Aircraft Engineering
Òàáëèöà 12
Ïîêàçàòåëü äîïóñêà íà àýðîäèíàìè÷åñêèé êîíòóð
¹
Äîïóñê íà àýðîäèíàìè÷åñêèé
êîíòóð
kàýð
1
0,5-0,8
0,2
2
0,8-1,0
0,4
3
1,0-1,5
0,6
4
1,5-2,0
0,8
5
2,0-3,0
1
Òàáëèöà 13
Ïîêàçàòåëü âûõîäà íà òåîðåòè÷åñêèé îáâîä
¹
Âûõîä íà îáâîä
kÒÊ
1
Âûõîäèò
0,5
2
Íå âûõîäèò
1,0
Òàáëèöà 14
Ïîêàçàòåëü ðàñïîëîæåíèÿ ýëåìåíòîâ
¹
Ðàñïîëîæåíèå ýëåìåíòîâ
kN
1
Îäíîñòîðîííåå
1,0
2
Äâóñòîðîíåå
0,8
Èñïîëüçóÿ ïðèâåäåííóþ âûøå ìåòîäèêó, íàõîäèì ïîêàçàòåëè ki ïðèìåíèòåëüíî ê êîíñòðóêöèè
äèàôðàãìû (çàïîëíÿåì òàáë. 1) è ñ ó÷åòîì êîýôôèöèåíòîâ âåñîìîñòè îïðåäåëÿåì ki ϕi . Êîýôôèöèåíòû âåñîìîñòè ïîêàçàòåëåé òåõíîëîãè÷íîñòè îïðåäåëåíû ýêñïåðòíûì ïóòåì. Äëÿ îöåíêè äðóãèõ äåòàëåé ïëàíåðà ìîãóò áûòü èñïîëüçîâàíû èëè âñå,
èëè ÷àñòü ïîêàçàòåëåé, à èõ êîýôôèöèåíòû âåñîìîñòè äîëæíû áûòü âûÿâëåíû íà îñíîâå íîâûõ ýêñïåðòíûõ îöåíîê. Ñóììà âûáðàííûõ êîýôôèöèåíòîâ âåñîìîñòè ðàâíÿåòñÿ åäèíèöå.
Òàêèì îáðàçîì, îïðåäåëÿåì êîìïëåêñíûé ïîêàçàòåëü òåõíîëîãè÷íîñòè äèàôðàãìû ïî ôîðìóëå (1)
0,787
= 0,787.
p=
1
 ðåçóëüòàòå ïðîâåäåííûõ ðàñ÷åòîâ ïîëó÷èëè
ñëåäóþùèå çíà÷åíèÿ òåõíîëîãè÷íîñòè äèàôðàãìû:
1) äëÿ íîâîé äåòàëè
0,5;
2) ðàññ÷èòàííîå ïî ìåòîäèêå 0,787.
Ñðàâíèâàÿ êîìïëåêñíûé ïîêàçàòåëü, ðàññ÷èòàííûé ïî ïðèâåäåííîé ìåòîäèêå, ñ áàçîâûì äëÿ íîâîé äåòàëè, ìîæíî ñäåëàòü âûâîä, ÷òî ïðîåêòèðóåìàÿ êîíñòðóêöèÿ äèàôðàãìû òåõíîëîãè÷íà è ìîæåò áûòü ïðèíÿòà äëÿ èñïîëüçîâàíèÿ â ïðîèçâîä-
ñòâåííûõ óñëîâèÿõ. Ïðåäëàãàåìàÿ ìåòîäèêà ïðîâåðåíà ïðè êîíñòðóèðîâàíèè øòàìïóåìûõ äåòàëåé èç
ëèñòà è îòðàæàåò ðåàëüíîñòü ïðîöåññà êîíñòðóèðîâàíèÿ è èçãîòîâëåíèÿ.
Ñëåäîâàòåëüíî, ïðåäëàãàåìàÿ ìåòîäèêà îòðàáîòêè êîíñòðóêöèè äåòàëè íà òåõíîëîãè÷íîñòü ìîæåò
óñïåøíî ïðèìåíÿòüñÿ íà ïðàêòèêå äëÿ ðàñ÷åòà ïðîèçâîäñòâåííîé òåõíîëîãè÷íîñòè è îöåíêè êà÷åñòâà
íîâûõ ðàçðàáàòûâàåìûõ äåòàëåé ïëàíåðà, äëÿ êîòîðûõ íà ðàííèõ ñòàäèÿõ òåõíîëîãè÷åñêîé ïîäãîòîâêè ïðîèçâîäñòâà îöåíêà óðîâíÿ òåõíîëîãè÷íîñòè ïî
îñíîâíûì ïîêàçàòåëÿì ñòàíäàðòà çàòðóäíèòåëüíà è
íåâîçìîæíà ââèäó íåïîëíîòû èíôîðìàöèè, à ïî
äîïîëíèòåëüíûì ïîêàçàòåëÿì — îãðàíè÷åíà, òàê
êàê îòðàæàåò òîëüêî êîíñòðóêòèâíûå ýëåìåíòû.
Ïðèìåíåíèå äàííîé ìåòîäèêè â ñèñòåìå àíàëèçà ÒÊÈ íà ðàííèõ ýòàïàõ ïðîåêòèðîâàíèÿ äåòàëåé
ïëàíåðà ïîçâîëÿåò ïðåîáðàçîâûâàòü ìîäåëè äåòàëåé
â óñëîâèÿõ èçìåíÿþùåãîñÿ ñëîâàðÿ òåõíîëîãè÷åñêîãî ïðåäñòàâëåíèÿ ïðè çíà÷èòåëüíîì ïîñòîÿíñòâå
ñëîâàðÿ êîíñòðóêòîðñêîãî ïðåäñòàâëåíèÿ. Âðåìåííîå èçìåíåíèå îáóñëîâëåíî ðàçâèòèåì òåõíîëîãèé
è ìåòîäîâ òåõíîëîãè÷åñêîãî ïðîåêòèðîâàíèÿ. Ïðåäëàãàåìàÿ ñèñòåìà àíàëèçà ÒÊÈ äîëæíà, ïî âîçìîæíîñòè, èçîëèðîâàòü êîíñòðóêòîðà îò ïðîñòðàíñòâåííî-âðåìåííûõ èçìåíåíèé òåõíîëîãè÷åñêîãî áàçèñà, íî ó÷èòûâàòü èõ ïðè ïîñòðîåíèè òåõíîëîãè÷åñêîé ìîäåëè äåòàëè.
Òàêèì îáðàçîì, ïðèìåíåíèå ñèñòåìû àíàëèçà
ÒÊÈ îáåñïå÷èâàåò àäàïòàöèþ ìåòîäà ê çàäàííîìó
ïðîèçâîäñòâó, àêêóìóëèðóÿ çíàíèÿ î òåõíîëîãè÷åñêîì áàçèñå ïðîèçâîäñòâà. Òåì ñàìûì îáåñïå÷èâàåòñÿ àäàïòèâíîñòü ìåòîäà â öåëîì, ó÷èòûâàþòñÿ
ñóáúåêòèâíûå è îáúåêòèâíûå îñîáåííîñòè ïðîèçâîäñòâà. Ìåòîä ðàñïîçíàâàíèÿ ðàáîòàåò ñ êîíñòðóêòîðñêèìè ìîäåëÿìè, ïîñòðîåííûìè òâåðäîòåëüíûìè ïðèìèòèâàìè, ÷åì îáåñïå÷èâàåò èíâàðèàíòíîñòü
ìåòîäèêè àíàëèçà ÒÊÈ ê ñïîñîáó ïîñòðîåíèÿ ìîäåëè.
Áèáëèîãðàôè÷åñêèé ñïèñîê
1.
2.
3.
4.
Àìèðîâ Þ. Ä. Òåõíîëîãè÷íîñòü êîíñòðóêöèè äåòàëè / Áèáëèîòåêà êîíñòðóêòîðà. — Ì.: Ìàøèíîñòðîåíèå, 1990. — 768 ñ.
ÃÎÑÒ 14.201-83. Îáùèå ïðàâèëà îáåñïå÷åíèÿ òåõíîëîãè÷íîñòè êîíñòðóêöèè äåòàëè. — Ì.: Èçäàòåëüñòâî ñòàíäàðòîâ, 1983.
Êîëãàíîâ È.Ì., Äóáðîâñêèé Ï.Â., Àðõèïîâ À.Í.
Òåõíîëîãè÷íîñòü àâèàöèîííûõ êîíñòðóêöèé, ïóòè
ïîâûøåíèÿ. ×àñòü 1: Ó÷åáíîå ïîñîáèå. — Óëüÿíîâñê: ÓëÃÒÓ, 2003. — 148 ñ.
Îñåòðîâ Â. Ã., Àìèðîâ Þ.Ä. Òåõíîëîãè÷åñêèé àíàëèç ìàøèíîñòðîèòåëüíîãî ïðîèçâîäñòâà. — Ì.: Ìàøèíîñòðîåíèå, 1980. — 205 ñ.
ÂÅÑÒÍÈÊ ÌÀÈ. Ò.20. ¹1
!#
Àâèàöèîííàÿ òåõíèêà
Aircraft Engineering
METHOD OF QUANTITATIVE ASSESSMENT OF THE AIRFRAME ELEMENT
MANUFACTURABILITY
Govorkov A.S.
Irkutsk state technical university (National Research University),
83, Lermontov st., Irkutsk, 664074, Russia
e-mail: [email protected]
n
Abstract
Purpose
Nowadays element design is carried out with the
help of CAD/CAM/CAE/PDM systems. Thus it is
rational to estimate the manufacturability of element
structure at early stages of product launch during element
design and manufacturing. The goal of this paper is to
provide a method for such evaluation. The paper
considers a method of manufacturability calculation and
estimation, which allows formalizing the process of
airframe element manufacturability evaluation and
altering characteristics and parameters of individual
indicators.
Design/methodology/approach
While refining the airframe element design with the
purpose of increasing the airframe manufacturability, one
must take into account the manufacturing type and
specific features of the manufacturer (manufacturing
plant) so that structure of individual elements could be
produced with taking the aforementioned factors into
account.
The paper proposes a method of quantitative
estimation
of
airframe
element
structure
manufacturability based on interaction of individual
indicators with taking into account their weightcoefficients. Also an algorithm for manufacturability
control of the element based on its 3D-model is
suggested.
Final assessment of industrial manufacturability is
carried out according to single individual indicators by
comparing the variants of the proposed element with
analogues, which are already manufactured at the
considered plant. The aggregated indicator value is
determined under the conditions of an extremely
unfavorable combination of individual indicators based
on expert estimates.
The quantitative assessment of element
manufacturability during its design is carried out with
the help of an aggregated indicator:
!$
ÂÅÑÒÍÈÊ ÌÀÈ. Ò.20. ¹1
p=
∑ ki ϕi
i =1
n
∑ ϕi
,
i =1
where ki is the value of
manufacturability indicator i;
individual
element
ϕi is the weight-coefficient of individual element
manufacturability indicator i;
n is the number of adopted indicators, which is
defined by the expert and must be no less than 5.
Weight-coefficients of the manufacturability
indicators are determined by experts. Part of the
indicators can be used again to evaluate other airframe
elements while their weight-coefficients should be reidentified based on new expert estimates.
Findings
It is difficult and often impossible to fully estimate
manufacturability level at early stages of manufacturing
process design because of insufficient information. To
ensure the structure manufacturability it is possible to
make a qualitative assessment via manufacturability
properties and carry out the quantified evaluation using
individual indicators.
The proposed method was tested on the example of
structure design of sheet pressed airframe elements. It
was discovered that this method does reflect the real
conditions of structure design and manufacturing
processes.
Research limitations/implications
The proposed method is based on expert estimations.
Thus additional work is required for selecting the
appropriate groups of experts to make these estimations
less influenced by subjectivity of particular personalities.
Originality/value
Proposed methodology of refining the element
structure manufacturability can be successfully applied
in practice for calculation of manufacturability and
Àâèàöèîííàÿ òåõíèêà
estimation of the quality of the new developed airframe
elements. This is especially important since it might be
hard and/or impossible to carry out the
manufacturability estimation for such elements according
to the main indicators of the standards at the early stages
of pre-production planning due to the lack of
information, while the ability to carry out the estimation
according to additional indicators is limited since such
estimation would only reflect the structural design aspect.
Technologies and methods of manufacturing design
change over time. The proposed system of
manufacturability analysis aspires to «isolate» the
designer from such changes while still taking them into
account during the creation of the model of the element
manufacturing process.
Application of structure manufacturability analysis
provides for adaptation of the method to the specific
manufacturing by accumulating knowledge about its
technological basis. This ensures adaptability of the
method as a whole and takes into account general and
particular characteristic features of manufacturing. The
recognition method works with structure models, which
are based on solid-body primitives, thus ensuring the
invariability of the manufacturability analysis method
towards the way the model was built.
Aircraft Engineering
References
1.
2.
3.
4.
Amirov Yu.D. Tekhnologichnost’ konstruktsii detali
(Element structure manufacturability), Moscow,
Mashinostroenie, 1990, 768 p.
Obshchie pravila obespecheniya tekhnologichnosti
konstruktsii detali, GOST 14.201-83 (GOST All-Union
State Standard 14.201-83. Common rules of providing
the element structure manufacturability, GOST 14.20183), Moscow, Standarty, 1983.
Kolganov I.M., Dubrovskii P.V., Arkhipov A.N.
Tekhnologichnost’ aviatsionnykh konstruktsii, puti
povysheniya (Aircraft structure manufacturability and
ways of its improvement), Ulyanovsk, UlGTU, 2003,
part 1, 148 p.
Osetrov V.G., Amirov Yu.D. Tekhnologicheskii analiz
mashinostroitel’nogo
proizvodstva
(Analysis
of
manufacturing technologies of machinery production),
Moscow, Mashinostroenie, 1980, 205 p.
Keywords: product model, manufacturability,
airframe structure element, individual indicator of
manufacturability, structure component.
ÂÅÑÒÍÈÊ ÌÀÈ. Ò.20. ¹1
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