In below figure shows an oil field pump mechanism. The head of the rocker arm is
ID: 3605654 • Letter: I
Question
In below figure shows an oil field pump mechanism. The head of the rocker arm is shaped such that the lower end of a flexible cable attached to it will always be directly over the well head regardless of the position of the rocker arm 4. The pump rod, which connects to the pump in the well casing, is connected to the lower end of the cable. The force in the pump rod on the up stroke is 2970 lb and the force on the down stroke is 2300 lb. Link 2 weighs 598.3 lb and has a mass moment of inertia of 11.8 lb-in-sec' (blob-in2); both include the counterweight. Its CG is on the link centerline, 13.2 in from O2. Link 3 weighs 108 lb and its CG is on the link centerline, 40 in from A. Link 4 weighs 2706 lb and has a mass moment of inertia of 10700 lb-in-sec"(blob-in, both include the counterweight. Its CG is on the link centerline where shown. The crank turns at a constant speed of 4 rpm cCW. To develop a Matlab Code for a) Determine the position, Velocity, and acceleration of point P also the acceleration in center of mass of each link when the crank turns a revolution, and plot vs angle of crank and also vs time. b) Determine the maximum forces in the pins, torque needed to drive and which crank angle is happens and the time. (Include gravity forces because the links are heavy and the speed is low To develop a model in CREO Parametric software and Compare your Plot code of position velocity and acceleration of point P for a revolution, and plot vs angle of crank and also vs time. The report will be delivered with a detailed documentation (Include hand calculation for some angle of crank) B-CG, = 32.00 P-CG4 124.44 04-CG,-79.22 51.26 156.6 counter weight head end CG 80 14.03 47.5 47.5- 76 cable 14 counterweight pump rod 0% well headExplanation / Answer
Syntax
position= planetEphemeris(ephemerisTime,center,target)
position = planetEphemeris(ephemerisTime,center,target,ephemerisModel)
position = planetEphemeris(ephemerisTime,center,target,ephemerisModel,units)
position= planetEphemeris(ephemerisTime,center,target,ephemerisModel,units,action)
[position,velocity] = planetEphemeris(___)
Description
example
position= planetEphemeris(ephemerisTime,center,target) implements the position of the target object relative to the specified center object for a given Julian date ephemerisTime. By default, the function implements the position based on the DE405 ephemerides in units of km.
The function uses the Chebyshev coefficients that the NASA Jet Propulsion Laboratory provides.
This function requires that you download ephemeris data with the Add-On Explorer. For more information, see aeroDataPackage.
position = planetEphemeris(ephemerisTime,center,target,ephemerisModel) uses the ephemerisModel coefficients to implement these values.
position = planetEphemeris(ephemerisTime,center,target,ephemerisModel,units) specifies the units for these values.
position= planetEphemeris(ephemerisTime,center,target,ephemerisModel,units,action) uses action to determine error reporting.
example
[position,velocity] = planetEphemeris(___) implements the position and velocity of a the target object relative to the specified center for a given Julian date ephemerisTime using any of the input arguments in the previous syntaxes.
Examples
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Implement Position of Moon
Implement the position of the Moon with respect to the Earth for December 1, 1990 with DE405:
Implement Position and Velocity for Saturn
Implement the position and velocity for Saturn with respect to the Solar System barycenter for noon on January 1, 2000 using DE421 and AU units:
Input Arguments
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ephemerisTime — Julian date
scalar | 2-element vector | column vector | M-by-2 matrix
Julian date for which the positions are calculated, specified as one of the following:
Scalar
Specify one fixed Julian date.
2-element vector
Specify the Julian date in multiple parts. The first element is the Julian date for a specific epoch that is the most recent midnight at or before the interpolation epoch. The second element is the fractional part of a day elapsed between the first element and epoch. The second element must be positive. The value of the first element plus the second element cannot exceed the maximum Julian date.
Column vector
Specify a column vector with M elements, where M is the number of fixed Julian dates.
M-by-2 matrix
Specify a matrix, where M is the number of Julian dates and the second column contains the elapsed days (Julian epoch date/elapsed day pairs).
Data Types: double
center — Reference body (astronomical object) or point of reference
'Sun' | 'Mercury' | 'Venus' | 'Earth' | 'Moon' | 'Mars' | 'Jupiter' | 'Saturn' | 'Uranus' | 'Neptune' | 'Pluto' | 'SolarSystem' | 'EarthMoon'
Reference body (astronomical object) or point of reference from which to measure the target barycenter position and velocity.
Data Types: char
target — Target body (astronomical object) or point of reference
'Sun' | 'Mercury' | 'Venus' | 'Earth' | 'Moon' | 'Mars' | 'Jupiter' | 'Saturn' | 'Uranus' | 'Neptune' | 'Pluto' | 'SolarSystem' | 'EarthMoon'
Target body (astronomical object) or point of reference of the barycenter position and velocity measurement.
Data Types: char
ephemerisModel — Ephemerides coefficients
'405' (default) | '421' | '423' | '430' | '432t'
Ephemerides coefficients, specified as one of these ephemerides defined by the Jet Propulsion Laboratory:
'405'
Released in 1998. This ephemerides takes into account the Julian date range 2305424.50 (December 9, 1599 ) to 2525008.50 (February 20, 2201).
This function calculates these ephemerides with respect to the International Celestial Reference Frame version 1.0, adopted in 1998.
'421'
Released in 2008. This ephemerides takes into account the Julian date range 2414992.5 (December 4, 1899) to 2469808.5 (January 2, 2050).
This function calculates these ephemerides with respect to the International Celestial Reference Frame version 1.0, adopted in 1998.
'423'
Released in 2010. This ephemerides takes into account the Julian date range 2378480.5 (December 16, 1799) to 2524624.5 (February 1, 2200).
This function calculates these ephemerides with respect to the International Celestial Reference Frame version 2.0, adopted in 2010.
'430'
Released in 2013. This ephemerides takes into account the Julian date range 2287184.5 (December 21, 1549) to 2688976.5 (January 25, 2650).
This block implements these ephemerides with respect to the International Celestial Reference Frame version 2.0, adopted in 2010.
'432t'
Released in April 2014. This ephemerides takes into account the Julian date range 2287184.5, (December 21, 1549 ) to 2688976.5, (January 25, 2650).
This block implements these ephemerides with respect to the International Celestial Reference Frame version 2.0, adopted in 2010.
Data Types: char
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