We can work on Spacecraft Stabilization Using Droplet Stream Momentum Transfer

Spacecraft Stabilization Using Droplet Stream Momentum Transfer
Satellite System
The satellite system selected for this project was the new electrospray thruster known as The Advanced ESPT-4. The design is desirable because it provides greater performance with minimal cost and easy accessibility. The primary mission of this system is to use the droplet stream momentum to stabilize a spacecraft. The secondary mission is to establish a satellite system that will help in servicing a satellite for controlling the orientation and/or alter the orbit of an uncooperative satellite.
Mission Requirements and Constraints
The design requirements yet to be integrated for the advanced ESPT-4 will rely on its application, which, is to improve performance. Consequently, the core requirements for the performance application will comprise achieving the biggest density of thrust, obtaining small impulse bits of an elevated accuracy for greater precision maneuvers, and bringing about emitter arrays that are densely packed (Micci & Ketsdever, 2000). The densely packed emitter arrays are 2-dimensional, consisting of multiple discrete emitters that lend to the scalability and modularity of the modern technology. The Advanced ESPT-4 will take 9 years to complete. The annual mission operation will be $2M, which amounts to a total cost of $18M. Within 45 months into initiation, the Advanced ESTP-4 will be launched to test initial orbit capability. All these requirements call only for few emitters to achieve the primary goals of the Advanced ESPT-4.
The project mission also has constraints pertaining to the design. The efforts to develop an electrospray thrust based on droplet stream momentum transfer can be constrained by the small size of the collector plate. The size of this component will have to be increased to ensure that all emissions are harnessed, depending on the specifics of propellant in use. Evading such a constraint will improve the functioning of the Advanced ESPT-4 and provide maximum spacecraft stabilization. With a total budget of $ 58.5M however, such constraints as the size of the collector plate will be effectively increase. A major schedule constraint in this project will be time limitation, that is, the dates to be adhered to will be no earlier or later than the specified dates.
Payloads
The payload of the Advanced ESPT-4 includes a total mass of 60kg, inclusive of the propellant mass. Optical telescopes (Galileo Galilei, 1609) will be used to show an overview of space and spectroscopes that will help in studying light’s wavelength. Space target identification which is a primary function and of critical importance to this project will be done on the basis of radar data partition and deep learning. For this satellite, the total cost of payload will amount to $10M. Further payload items are listed in table 1.
Orbit and it’s COEs
Since satellites often lose track of their orbits, the Electrospray thruster satellite systems will help in maneuvering of unfamiliar orbits (Grush, 2020). The advanced ESPT-4 will pursue the Hohman transfer orbit, which, minimize acceleration (∆v). The choice of Hohman transfer orbit refers to the orbit’s benefit of being the most fuel efficient and ideal way to opt for the Advanced ESPT-4.
Attitude Determination and Control System (ACDS)
The Advanced ESPT-4 will be able to have access to sensors for the determination of attitude and automatically apply correction through Actuators. If everything functions accordingly, a confirmation will be sent to the OBC. In order to stabilize the satellite, kinetic energy of the whole system will have to be decreased using properties of the auctors. Correct supply of the magnetorquers will generate a Torque
Equation of the Torque developed will be; T= m ^ B
Where m= magnetic moment of the dipole
B is the magnetic field of earth.
Therefore, this means that the Advanced ESPT-4 satellite will have the ability to align itself with the earth magnetic field since it will be completely linked with both.
Power sub system
Solar energy as the form of electrical power sub system in the Advanced ESPT-4 is being highly considered due to its availability as it encourages the development of solar cell arrays which are key structural element for provision of power generation. Institution of Soar Array Design will be carried out during development. Installation of this power sub system will need $2 M and will be completed within 3 months.
Mission concept of operations
There will be a total of seven stakeholders in designing the Advanced ESPT-4 as in Table 3. Stakeholders directly involved with the project includes operators, payload and service providers, and integrators. Additional parties are the guaranteed customers and community collaborators. Satellite information will be transferred through satellite images to the professionals who will further interpret them to find paths.

Schedule
The mission design and analysis will take 6 months. Afterwards, the payloads and spacecraft bus will run consecutively each taking a month. The advances ESPT-4 will be assembled and integrated for 6 months. Installation of a power sub system will take 3 months. The project will then be tested for six months, also after which the launch campaign will proceed for 4 months. The Gantt chart in table 3 visualizes the project schedule.
Budget
The project budget sums up to $58.5M as in table 4. The Advanced ESPT-4 payloads and the ground station will cost $10M and $2.5M respectively. The total operating cost will ne $4M. It will take another $10M to assemble and integrate the design. Furthermore, the payload and spacecraft bus will need $16M to complete. Solar array technology power sub system will need $ 2MFinally, testing and launching. The Advanced ESPT-4 will need $14M in total. Further assumptions, as In Table 5, include structure costs of $25,000 and EPS of $400,000. Both ADCS and propulsion will cost a total of $445,000 while CDHS will need $180,000.
Summary
The designed system is primarily aimed at enhancing the stability of spacecraft by the use of the droplet steam momentum transfer. An electrospray thruster was selected for this project. The requirements for performance application of the system were found to be attaining the largest density of thrust, getting small impulse bits of a high accuracy for greater precision, and having emitter rays that are densely packed. The initial orbit capability of the system was shown within 45 months.

Part 2
The Hohman Transfer
The Hohman transfer orbit from Earth to Mars has;
2a=48.94106m, E=-8.144106 m2/s2 (J/Kg)
The resultant E is therefore E1<E<E2.
The velocity at the pedigree and apogee will be;
VX=10, 130m/s and va=1,067 m/s respectively.
The specific angular motion is; h=6.787*1010m2/s
While the eccentricity e=0.7265
The final impulses required are ∆vx=2414m/s
∆va=1465m/s which sum up to;
∆vr=3882m/s
The time of flight (TOF) translates to 5.29hours.
To calculate the possible time for lunar and solar eclipse, the formula;
∆T=62.93+0.32217 *t+0.005589 *t2 will be used
Where;
y=year+ (month-0.5)/12
t=y-2000.

Launch Site
In this specific project design, the desired launch site that will be used is the NASA Goddard Space Flight Centre’s Wallops Flight Facility. This sight is located 37˚ 51’N, 75˚ 28’W with azimuths ranging from 90˚-160˚, since the Wallops Flight Facility supports researchers from NASA and other institutions like educational and international, it will be appropriate.
Testing
As much as The Advanced ESPT-4 cannot be damaged since it will eventually be launched in the Hohman transfer orbit, it will be important to test the Advanced ESPT-4 using swept sine. This testing method will be a vital procedure in qualifying the satellite for launch. Swept Sine testing will involve focusing on a specific structure within the satellite using a single frequency. The Advanced ESPT-4 will include a higher channel count that will require the use of a different analysis system will be featured therefore no need to use a dynamic signal analyzer. This will help in identifying all the weak spots that might be a problem during launch. Total testing amount for this satellite will be $450,000 as shown in table 4 in a duration of 6 months.
Space Environment
The Advanced ESPT-4 will be among other satellites launched to space. There are radiation hazards that satellites like this face while in space. The effects of radiation on this satellite project will be managed through shielding. For shielding, the design will need either tantalum or tungsten shields. Under High radiation, space environments, the project may opt to use additional aluminum layer as a way of reducing dose enhancement (Maurer et al., 2008.). In case of cosmic rays, the design will ensure minimal shielding is done so that the rate of SEEs can be managed. Other techniques that will be considered for this project are conservative design, limited view angles and substantial characterization.
Spacecraft charging, and extreme temperatures are other hazards that the satellite may face in face. Spacecraft charging can, when built up either on the surface or the internal of the material, current can be compromised leading to catastrophic destruction of sensitive parts in the satellite. Extreme temperatures can result in reflection, refraction or absorption of radio waves. They can also result in expansion of the upper atmosphere which is usually denser at high attitudes hence putting a drag on orbiting satellites.
Budget
Additions to the budget that will be incurred include shielding costs of $80,000, testing cost of $450, 000 and another$105,000for creative new conservative design.

Summary
The desired launch site for the advanced ESPT-4will be the Wallops Flight Facility. The satellite will be launched expecting a TOF of 5.29 hours. Mitigan strategies especially shielding will also be implemented to ensure minimal radiation effects on the satellite.
Table 1.
Description Payload Units
Total mass 30 Kgs
Propellant mass 30 Kgs
Total power 30 W
Specific Impulse (ISP) 1 Sec
Voltage 2 kV
Emitter current 800 N
Thrust force 0.001 uA
Cost 10 $M
Delivery 15 Months

Table 2
Stakeholders Description of information
Satellite operators Ground and space interfaces
Customers Schedule, performance, as well as price concerns
Payload providers Spacecraft interfaces and resources
Integrators Interfaces compatibility, modularity, and interop ability
Insures The reduncy and reliability of the spacecraft system
Community collaborators Performance applicability and performance as well as the mission

Table 3: Gant chart

Table 4:
Item Amount in $M
Payload of the Advanced ESPT-4 10
Ground station cost 2.5
Mission operation cost ($2 per year) 4
Assembly and integration 10
Spacecraft bus 16
Testing 2
Launching 14
Total 58.5
Additional cost
Shielding o.08
Conservative design 0.105
New total 60.685

Table 5
Assumptions Cost ($M)
Structure 25,000
EPS 400,000
ADCS 350,000
Propulsion 95,000
Power sub system 450,000
CDHS 180,000
Launch Vehicle 300,000
Total 1,800,000

Final Report
The Advanced ESPT-4 will use droplet stream momentum to stabilize spacecraft as its primary function and help in establishing a system that will help in servicing a satellite for controlling the orientation and/or alter the orbit of uncooperative satellite as its secondary function. The design requirements will rely on its application, that is, improvement of performance. Consequently, core requirements for the performance application will comprise achievement is the biggest density of thrust, obtaining small impulse bits of an elevated accuracy for greater precision maneuvers and bringing about emitter arrays that are densely packed. Small size of collector plates and time limitation are the constraints in the development of an electrospray thrust based on droplet stream momentum transfer. The total budget will be $58.5M. With the propellant mass included, the payloads will be 60kgd. Optical telescope and spectroscopes will be used. Space target identification will be based on radar data partition and deep learning. The total payload cost will be $20. Solar array design will be used as the power sub system. This will take a period of 3 months and cost a total of $450,000
The advanced ESPT-4 will pursue the Hohman transfer orbit, which minimizes acceleration and is beneficial in terms of fuel conservation. ACDS will also be featured where sensors will determine attitude and Actuators to automatically do any correction. It will have a total of seven shareholders who are involved in designing. Satellite information will be transferred through satellite images to the professionals who will further interpret them to find paths. Mission design and analysis will take six months. Payloads and spacecraft bus will run consecutively each taking 1Moth. Testing will take six months and launching will afterwards proceed for 4 months.
Launch site will be NASA Godward Spaceflight Center’s Wallops Flight facility since it supports researchers from NASA and other educational and international institutions.
Space environment hazards include radiation, spacecraft charging and extreme temperatures. Advanced ESPT-4 has a functional design that will help in effectively managing these hazards. Testing of the satellite will be done through swept sine testing as it is the most convenient in terms of the satellite’s durability.

References
Grush, L. (2020). Northrop Grumman just launched its second satellite rescue mission. Retrieved from https://www.theverge.com/2020/17/21366674/northrop-grumman-space-logistics-mey-2-satellite-servicing-life-extension
Jackson, S. (2017). NASA’s CubeSat launch initiative. Retrieved from https://www.gov/directorates/heo/home/CubeSats_initiative
Joslyn, T. (n.d). Droplet stream momentum transfer for spacecraft stabilization. Omitron, Inc.
Maurer, R. H., Fraeman, M. E., Martin, M. N., & Roth, D. R. (2008). Harsh Environments: Space Radiation, Effects, and Mitigation. John Hopkins APL technical digest, 28(1), 17. https://www.researchgate.net/publication/241250936
Micci, M. M. & Ketsdever, A. D. (2012). Micropropulsion for Small Spacecraft. Progress in Astronautics and Aeronautics, 187. https://doi.org/10.2514/44.866586
Tummala, A.R. & Dutha, A. (2017). An overview of Cube-Satellite propulsion technologies and trends. Aerospace, 4(58), 1-30.
Unknown A, Attitude Determination and Control Analysis (ADCS)
www.ece3sat.com/cubesatmodules/adcs/
Unknown A, What Is Satellite Testing? November 19, 2018
www.nts.com/ntsblog/what-is-satelite-testing/