NAE1 Antibodies

NEDD8-activating enzyme E1 regulatory subunit (NAE1)

Regulatory subunit of the dimeric UBA3-NAE1 E1 enzyme. E1 activates NEDD8 by first adenylating its C-terminal glycine residue with ATP, thereafter linking this residue to the side chain of the catalytic cysteine, yielding a NEDD8-UBA3 thioester and free AMP.

E1 finally transfers NEDD8 to the catalytic cysteine of UBE2M. Necessary for cell cycle progression through the S-M checkpoint.

Gene Information

Human
Gene Name:	NAE1
Uniprot:	Q13564
Entrez:	8883

Family

Belongs to:
ubiquitin-activating E1 family

Alternative Names

A-116A10.1; amyloid beta precursor protein binding protein 1; amyloid beta precursor protein binding protein 1, 59kDa; Amyloid beta precursor protein-binding protein 1, 59 kDa; amyloid beta precursor protein-binding protein 1, 59kD; Amyloid protein-binding protein 1; APPBP1APP-BP1; NEDD8 Activating Enzyme (APPBP1/UBA3); NEDD8 activating enzyme E1 subunit 1; NEDD8-activating enzyme E1 regulatory subunit; NEDD8-activating enzyme E1 subunit; protooncogene protein 1; Proto-oncogene protein 1; ula-1

Molecular Weight

Mass (kDA):
60.246 kDA

Genomic Context

Human
Location:	16q22.1
Sequence:	16; NC_000016.10 (66802878..66830977, complement)

Tissue Specificity

Ubiquitous in fetal tissues. Expressed throughout the adult brain.

Subcellular Localizations

Cell membrane. Colocalizes with APP in lipid rafts.

Diseases

• Transient Cerebral Ischemia
• Ischemia
• Malignant Neoplasm Of Breast
• Occlusion, Middle Cerebral Artery
• Neurofibromatosis 1
• Arterial Occlusion
• Chickenpox
• Exanthema
• Malignant Neoplasms
• Mammary Neoplasms

• Cerebral Artery Occlusion
• Transient Ischemic Attack
• Cerebral Ischemia
• Transient Ischemia

Pathways

• Neurogenesis
• Rna Interference
• Conjugation

PTMs

• Acetylation

• Ubl conjugation

Research Areas

• Apoptosis

For details, visit:
bosterbio.com/bosterbio-gene-info-cards/NAE1

Best Uses Of The NAE1 Marker

Steven Boster invented his first product in 1993. He earned the name "he who transforms science into the lavatory." Boster has been creating many products since 1993 including ELISA kits and IHC Reagents and hundreds of primary antibodies. Boster was China's top antibody catalog company by the end of the 1990s. Additionally, Boster developed a proprietary ELISA platform, PicoKine(tm), which provides high-sensitivity ELISA kits.

Simulations of ZGSP rendezvous

The simulations in this paper are based on closed-loop methods and rely on PMD sensor images to determine the position and speed of rotation of the target. Two robots were used to perform rendezvous simulations. One is moving along the rail system, and the other is fixed to the end. The fixed robot is equipped with satellites that are mockups, while the other one has an Argos3D camera equipped with a PMD sensor.

These algorithms can be employed in conjunction with particle simulation programs LAMMPS and SPARTA. The simpler brute-force algorithm had been too slow for larger problems on modern machines and rendezvous algorithms can be implemented at a larger scale. This means that LAMMPS and SPARTA can now count bond topologies in molecular systems with billions of atoms, and their grid/surface intersections can be calculated by using millions of surface elements. These simulations can be utilized in many grid-based codes.

For two rigid bodies participating in a rendezvous maneuver an algorithm for two-phase proportional navigation was developed. To determine a trajectory the control algorithm relies on relative velocity and distance between the spacecraft that is chasing and the spacecraft of the target. It is also proven that a general formula for the reference relative trajectory is constructed for four types of proximity maneuvers. The transverse navigation constant is required for the subsequent phase.

Simulations of EO-1 formation flying

The formation flying mission of EO-1 was an engineering experiment to demonstrate how different satellites react to each one another in orbit and keep close proximity. Scientists also had the chance to combine different kinds of scientific data from several satellites. The satellite was launched as part of a science mission on the 21st of November 2001. It was designed to fly in formation along with Landsat-7.

EO-1 was launched by NASA as part of NASA’s New Millennium Program. It proved to be a great test site for the development of new technologies for future Earth-observing spacecraft. The mission validated a variety of technologies that can greatly enhance the capabilities and decrease the cost of future missions. For instance, EO-1's latest instruments, which include the Enhanced Thematic Mapper, collect multispectral images and coordinate with Landsat 7's Enhanced Thematic Mapper, will be used in follow-on missions.

Formation flying software uses information from the onboard GPS and maneuver algorithm to provide pointing and commanding of thrusters. This technology is an effective tool that allows scientists to launch and manage multiple EO satellites simultaneously, while preserving their positions relative to other satellites. It permits shorter baselines between satellites, and it can also combine multiple satellites into a single virtual satellite, which can provide unmatched scientific data.

Simulations of Landsat-7 Formation Flying

Formation flying is a useful method of Earth observation and is commonly employed by meteorologists, astronomers as well as scientists studying climate and environmental science. An array can be made from multiple satellites positioned at different distances. Interferometry can improve the resolution of satellite data. Additionally, JPL is planning a project known as Starlight, which will employ a series of space telescopes to gather data from Earth. The SIM mission that utilizes multiple spacecraft, is another mission that will use multiple spacecraft. It is scheduled to launch in the year 2009.

Utilizing GPS and general equations of relative orbit dynamics, we have developed a novel approach to autonomous control of multiple spacecraft that are in formation. We also present an approach to implement this method by using discrete-time linear optimal output feedback control. We also explore the use of pulse-amplitude modulation in actuators. We present simulation results for an simulated EO-1 Landsat 7 formation. This will enable us to see how well the new approach works in practice.

The EO-1 is fitted with a Tensor GPS receiver manufactured by Space Systems/Loral. The Tensor GPS receiver integrates directly into the C&DH. It retrieves data and creates commands. The AutoConTM system is a combination of only the objects that are required to make precise observations and is compatible with a variety of onboard navigation systems. The AutoConTM system allows spacecraft to autonomously perform formation control maneuvers.

MWR was tested on a 6-DOF moving platform. We validated the accuracy specifications to micron level. The results demonstrate that MWR can be used in real space formation missions in the future. The results of the MWR test highlight the key design parameters of the ranging system. The simulation results reveal the precision of the submillimeter-level ranging accuracy by using an adaptive filter. The adaptive filter takes into account the uncertainty resulting from the process noise into the signal.

Simulations of the TDRS-3 rendezvous

In the first scenario, simulations of TDRS-3 rendezvous using NAE1 markers are conducted under the conditions of solar eclipse. The TDRS-1 is now in a lower orbit than was originally intended to be. The tiny ACS thrusters enable the TDRS-1 to move itself into GEO. The second scenario describes simulations of TDRS-3 rendezvous using the same data.

The simulations are based on a baseline plan that disables GPS navigation data during slews. The Delta-V magnitude of the TTI is then modelled as a direction based on the velocity vector that is instantaneous. The TDRS-3 reentry operation was then conducted. The mission was successful. TDRS-3 rendezvous with the NAE1 marker was successfully accomplished.

The TDRS-3 thruster has three tethers to allow pitch and unloading yaw. A second mechanism is IMAGE. In this scenario the thrusters have to be operated at a low body rate. Once the thrusters are in operation, they are declared functional. A rendezvous with the R-bar nominal is also planned for SM3A.

The satellite antenna module TDRS-3 consists of four S-band/Ku-band deployable parabolic antennas. Each antenna has dual-feed capability. The primary reflector surface is a gold-clad molybdenum mesh. The antennas fully deployed cover an area of 44 feet by 16.3 feet. Additionally, the TDRS-3 satellites are able to detect the signals of up to 25 users.

The TDRS-3 mission planners use this technique to minimize the retrospective observation uncertainty. A model of the IMAGE spacecraft can be used to calculate alignment of the gyro and the attitude. This model is suitable for other spacecraft whose inclination is determined by the gyro's direction. Simulations of TDRS-3 rendezvous using NAE1 markers provide valuable insights to enhance mission planning.

In addition to the TDRS-3 trajectory The models also allow more in-depth analysis of the collision parameters. The parameters used in the study are meant to represent average values and cannot be predicted with confidence. The models that are generated don't include explosions, which cannot be predicted without a thorough blast analysis. Hence, they are designed for use in a constrained space.