In this paper, the design, fabrication and testing of an integrated three-axis magnetic torque on the cube satellite driver range in accordance with the requirements of ISIS's external sample. Based on the specified mission requirements, magnetic torque generators generate a magnetic field around the satellite that interacts with the Earth's magnetic field and produces a torque on the satellite, so that the satellite's angular momentum can be changed and controlled. The use of these actuators in the status control system has advantages such as no need for fuel (such as thrusters), low power consumption, lack of moving parts and is especially popular in cubic satellites. The focus of the design space is on maximizing the magnetic dipole moment to find the response vector, including the number of turns, the length and radius of the core, and the number of turns and dimensions of the non-magnetic nucleus for the air core. The design of the windings based on the optimization method of sequential quadratic SQP programming under the constraints of inequality requirements such as mass, power, etc. has been done with the aim of achieving a magnetic dipole moment of 0.2 Am2. This three-axis integrated torques with their integrated drivers were calibrated by Honeywell's HMR2300 magnetometer sensor after measuring the generated magnetic field using a magnetic dipole moment relationship. The results show that the specifications of the designed sample are met.

Hash functions have a very important role in network and telecommunication security. These functions play an important role in hashing a message which are widely used in cryptographic applications such as digital signatures, random number generator algorithms, authentication protocols, and so on. Rotational cryptanalysis is a relatively new attack that is part of a generic attack on hash functions and is effective on algorithms that have an ARX structure. In this paper, for the first time, we apply a rotational cryptanalysis and with the given assumption of the markov chain for the modular additions sequence employed in two algorithms Shabal and CubeHash, which are second-round candidates for the SHA-3 competition that use the ARX property in their structure. With the implementation of rotational cryptanalysis we arrived at the complexity of 2-3393. 58 for the entire 16+3-rounds Shabal algorithm and the complexity of 2-57. 6 for the en-tire 16-round CubeHash algorithm. According to the obtained results, it can be seen that due to the large number of modular additions with the given assumption of markov chain, the Shabal algorithm exhibits greater resistance to rotational cryptanalysis, compared to the CubeHash algorithm and is less likely to succeed.

A nontrivial graph is called nicely distance-balanced (nicely edge distance-balanced), whenever there exist positive integers γ _V (γ _E), such that for any adjacent vertices u and v in V(Γ ), there are exactly γ _V vertices in V(Γ ) (γ _E edges in E(Γ ) that are closer to u than v, and exactly γ _V vertices in V(Γ ) (γ _E edges in E(Γ )) that are closer to v than u. In this paper, we will prove that hyper cube Q_n and the folded cube F_n are nicely distance-balanced and Q_n is also nicely edge distance-balanced. A nontrivial graph is called nicely distance-balanced (nicely edge distance-balanced), whenever there exist positive integers γ _V (γ _E), such that for any adjacent vertices u and v in V(Γ ), there are exactly γ _V vertices in V(Γ ) (γ _E edges in E(Γ ) that are closer to u than v, and exactly γ _V vertices in V(Γ ) (γ _E edges in E(Γ )) that are closer to v than u. In this paper, we will prove that hyper cube Q_n and the folded cube F_n are nicely distance-balanced and Q_n is also nicely edge distance-balanced.

Some contemporary logicians have introduced a new simple method of logical consequences and reduced all immediate arguments to Conversion and Obversion. By dint of positive and infinite terms, one of the logicians, Reza Akbari, increased the four traditional quantified propositions to 32 ones: the 4 well-known positives, 4 subject-infinites, 4 predicate-infinites, 4 two-sided-infinites, and the same 16 with ‘A’ and ‘B’ in which converted. Akbari, also, stated among some of the 32 propositions the interrelations: the opposition square, conversion, conversion by contradiction, obversion, inversion, and two new relations: “contraposition of the subject” and the “unknown”. This theory extending the classical 4-quntified-theory can be named “32-quntified-theory”. In this paper, I show that the 32 propositions are equivalent four-by-four, hence, we can reduce the 32 propositions to 8 ones and their relations to the six: equivalence, implication, inconsistency, inclusive ‘or’, exclusive ‘or’ and none (which is the same as Akbari’s “unknown”. By this, I decrease the perplexities of the theory and express so easily and elegantly the relations between the eight in a cube similar to the “Square of Opposition,” which I call the “Cube of Opposition.”

In this paper, a step-by-step laboratory procedure for performing a satellite's payload’s alignment measurement is presented. Four highly accurate theodolites are used along with two or more alignment corner cube to accurately extract the final attitude. Theodolites are arranged around the satellite in such a way that they have a clear direct view of the alignment cubes mounted on the payload and the satellite. Two theodolites should point to the payload’s alignment cube and the other two theodolites must point to the satellite’s alignment cube. Each theodolite must see at least one other theodolite, directly. Finally, by forming the coordinates systems of the payload and satellite in the theodolites coordinate system along with using the coordinate transfer matrices, the payload alignment correction matrix will be extracted in detail. The total method accuracy is within the order of few arcseconds.

In complicated systems such as satellites, each subsystem's design can affect the design of the overall system. In the design procedure, the effect of each technology on the other components should be determined. Because of increasing in space trash, the propulsion subsystems are introduced to avoid collision in space. One of the methods to attain high altitude orbits is flight maneuvers using propulsion systems. Several types of propulsion systems are utilized in satellites. Resistojets can be employed as a low-cost propulsion systems for satellites because they do not use complicated technologies. In the present research, a resistojet propulsion system is designed for a CubeSat for the mission of orbital altitude reduction. The propellant is selected according to all properties. The design of the nozzle and the heater is also introduced, The overall layout of the system is presented and finally, an algorithm of electrical propulsion systems for a specified mission is proposed.