Rockets use inertial measurement units and star trackers for takeoff orientation
the verdict
INSUFFICIENT LEANING
refutedsupported
the weight of evidence
5 sources for · 0 against
The retrieved evidence partially supports individual components of the claim by noting that rockets and spacecraft use inertial measurement units and star trackers for orientation or navigation, but no single source establishes both components acting together specifically for takeoff orientation.
calculate current position (e.g. compass, GPS, LORAN, star tracker, inertial measurement unit, and altimeter). In aircraft, successful air navigation involves
Flight or flying is the motion of an object through an atmosphere or through the vacuum of space, in this case also called spaceflight, without contacting any planetary surface. This can be achieved by generating aerodynamic lift associated with gliding or propulsive thrust, aerostatically using buoyancy, or by ballistic movement.
Many things can fly, from animal aviators such as birds, bats and i
There are different approaches to flight. If an object has a lower density than air, then it is buoyant and is able to float in the air without expending energy. A heavier than air craft, known…
A…
Vehicles that can fly can have different ways to takeoff and land. Conventional aircraft accelerate along the ground until sufficient lift is generated for takeoff, and reverse the process for landing. Some aircraft can take off at low speed; this is called a short takeoff. Some aircraft such as helicopters and Harrier jump jets can take off and land vertically. Rockets also usually take off and land vertically, but some designs can land horizontally.
Essentially, an extreme form of ballistic flight, spaceflight is the use of space technology to achieve the flight of spacecraft into and through outer space. Examples include ballistic missiles, orbital spaceflight, etc.
Spaceflight is used in space exploration, and also in commercial activities like space tourism and satellite telecommunications. Additional non-commercial uses of spaceflight include space observatories, reconnaissance satellites and other Earth observation satellites.
A spaceflight typically begins with a rocket launch, which provides the initial thrust to overcome the force of gravity and propels the spacecraft from the surface of the Earth. Once in space, the motion of a spacecraft—both when unpropelled and when under propulsion—is covered by the area of study called astrodynamics. Some spacecraft remain in space indefinitely, some disintegrate during atmospheric reentry, and others reach a planetary or lunar surface for landing or impact.
There are different approaches to flight. If an object has a lower density than air, then it is buoyant and is able to float in the air without expending energy. A heavier than air craft, known as an aerodyne, includes flighted animals and insects, fixed-wing aircraft and rotorcraft. Because the craft is heavier than air, it must generate lift to overcome its weight. The wind resistance caused by the craft moving through the air is called drag and is overcome by propulsive thrust except in the case of gliding.
Some vehicles also use thrust in the place of lift; for example rockets and Harrier jump jets.
A fixed-wing aircraft generates forward thrust when air is pushed in the direction opposite to flight. This can be done in several ways including by the spinning blades of a propeller, expanding exhaust pushed from the back of a jet engine, or by ejecting hot gases from a rocket engine. The forward thrust is proportional to the mass of the airstream multiplied by the difference in velocity of the airstream. Reverse thrust can be generated to aid braking after landing by reversing the pitch of variable-pitch propeller blades, or using a thrust reverser on a jet engine. Rotary wing aircraft and thrust vectoring V/STOL aircraft use engine thrust to support the weight of the aircraft, and vector sum of this thrust fore and aft to control forward speed.
Thrust-to-weight ratio is, as its name suggests, the ratio of instantaneous thrust to weight (where weight means weight at the Earth's standard acceleration
g
0
{\displaystyle g_{0}}
). It is a dimensionless parameter characteristic of rockets and other jet engines and of vehicles propelled by such engines (typically space launch vehicles and jet aircraft).
If the thrust-to-weight ratio is greater than the local gravity strength (expressed in gs), then flight can occur without any forward motion or any aerodynamic lift being required.
If the thrust-to-weight ratio times the lift-to-drag ratio is greater than local gravity then takeoff using aerodynamic lift is possible.
Flight dynamics is the science of air and space vehicle orientation and control in three dimensions. The three critical flight dynamics parameters are the angles of rotation in three dimensions about the vehicle's center of mass, known as pitch, roll and yaw (See Tait-Bryan rotations
It takes energy to create thrust (to gain height) and to push through the air (to overcome the drag associated with lift). Flighted creatures and objects vary in the efficiency of their muscles/motors and in how well this translates into forward thrust.
Propulsive efficiency determines how much energy vehicles generate from a unit of fuel.
The range that powered flight articles can achieve is ultimately limited by their drag, as well as how much energy they can store on board and how efficiently they can turn that energy into propulsion.
For powered aircraft the useful energy is determined by their fuel fraction- what percentage of the takeoff weight is fuel, as well as the specific energy of the fuel used.
Vehicles that can fly can have different ways to takeoff and land. Conventional aircraft accelerate along the ground until sufficient lift is generated for takeoff, and reverse the process for landing. Some aircraft can take off at low speed; this is called a short takeoff. Some aircraft such as helicopters and Harrier jump jets can take off and land vertically. Rockets also usually take off and land vertically, but some designs can land horizontally.
A guidance system is a device or group of devices used in the navigation of a ship, aircraft, missile, rocket, satellite, or other moving object. Typically, guidance is responsible for the calculation of the vector (i.e., direction, velocity) toward an objective.
entering the wrong codes, causing the inertial measurement unit (IMU) to register the module as having the same orientation it did before liftoff. The IMU then
James Arthur Lovell Jr. ( LUV-əl; March 25, 1928 – August 7, 2025) was an American astronaut, naval aviator, test pilot, and mechanical engineer. In 1968, as command module pilot of Apollo 8, he, along with Frank Borman and William Anders, became one of the first three astronauts to fly to and orbit the Moon. He then commanded the Apollo 13 lunar mission in 1970 which, after a critical failure en
As CMP, Lovell served as navigator, using the spacecraft's sextant to determine its position by measuring star positions. These measurements were used to calculate required mid-course corrections. During otherwise idle time, he conducted navigational sightings, maneuvering the module to view stars and entering data via the Apollo Guidance Computer keyboard. During one of these data entries, Lovell accidentally erased some of the computer's memory by entering the wrong codes, causing the inertial measurement unit (IMU) to register the module as having the same orientation it did before liftoff. The IMU then initiated thruster firings to "correct" for this newly registered attitude.
After identifying the issue, the crew knew that they would have to reenter the orientation data. Lovell took about ten minutes to calculate the correct values, using the thrusters to align the stars Rigel and Sirius in the sextant, and another 15 minutes to enter the correct measurements into the computer. The experience later proved valuable during Apollo 13, when Lovell had to perform a similar manual realignment under critical conditions after the IMU had been turned off to conserve energy.
A feature on the Moon's surface (Mount Marilyn) was named by Lovell in honor of his wife.
The spacecraft splashed down safely before dawn on December 27 after 147 hours of flight, 4.8 kilometers (2.6 nmi; 3.0 mi) from the recovery ship, the aircraf
The Gemini 6 mission, which was commanded by Schirra with Tom Stafford as pilot, had a serious setback on October 15, 1965, when the Agena target vehicle that Gemini 6 was supposed to rendezvous with exploded soon after takeoff. Lovell was present at the Launch Control Center at Cape
supposed to wind up the Gemini program and catch all those items that were not caught on previous flights." By July, its mission had become to master extravehicular activity (EVA), something that had proven problematic on earlier Gemini missions, as they had been more strenuous than expected and performing simple tasks had been more complicated. A series of innovations had been developed in response to the problems that had been encountered. It had been found that moving in space was similar to being underwater, and Aldrin made use of this new training technique.
A lunar orbital flight, now Apollo 8, replaced the original Apollo 9 medium Earth orbit test mission. The crew was informed of this decision on August 10, 1968, and the training schedule was adjusted accordingly. Starting in September, the crew spent ten hours a day in the simulator rehearsing the mission. Apollo 8 was launched on December 21, 1968, and Borman, Lovell and Anders became the first crew to ride the Saturn V rocket, as well as the first to travel to the Moon. Their Apollo craft entered lunar orbit on December 24 (Christmas Eve) and reduced speed to go into a 10.9-by-312.1-kilometer (5.9 by 168.5 nmi; 6.8 by 193.9 mi) orbit.
The engine was then fired again to enter a 111-kilometer (60 nmi; 69 mi) circular orbit around the Moon. On Christmas Eve, the crew broadcast black-and-white television pictures of the lunar surface back to Earth. Lovell took his turn with Borman and Anders in reading a passage from the Biblical creation story in the Book of Genesis. They made a total of ten orbits of the Moon in 20 hours and ten minutes, and began their return to Earth on December 25 (Christmas Day) with a rocket burn made on the Moon's far side, out of radio contact with Earth.
When contact was re-established, Lovell broadcast, "Please be informed, there is a Santa Claus." As CMP, Lovell served as navigator, using the spacecraft's sextant to determine its position by measuring star positions. These measurements were used to calculate required mid-course corrections. During otherwise idle time, he conducted navigational sightings, maneuvering the module to view stars and entering data via the Apollo Guidance Computer keyboard. During one of these data entries, Lovell accidentally erased some of the computer's memory by entering the wrong codes, causing the inertial measurement unit (IMU) to register the module as having the same orientation it did before liftoff.
The IMU then initiated thruster firings to "correct" for this newly registered attitude. After identifying the issue, the crew knew that they would have to reenter the orientation data. Lovell took about ten minutes to calculate the correct values, using the thrusters to align the stars Rigel and Sirius in the sextant, and another 15 minutes to enter the correct measurements into the computer. The experience later proved valuable during Apollo 13, when Lovell had to perform a similar manual realignment under critical conditions after the IMU had been turned off to conserve energy. A feature on the Moon's surface (Mount Marilyn) was named by Lovell in honor of his wife.
The heaters were left on for eight hours, and while this successfully purged the oxygen, it also removed teflon insulation from the copper electrical wiring. Liquid oxygen rapidly turned into a high-pressure gas, which burst the tank and caused the leak of a second oxygen tank. In just over two hours, all onboard oxygen was lost, disabling the hydrogen fuel cells that provided electrical power to the Command/Service Module Odyssey. Apollo 13 was the second mission not to use a free-return trajectory, so that they could explore the western lunar regions.
The article presents the analysis of the impact point dispersion reduction using lateral correction thrusters. Two types of control algorithms are used and four sources of uncertainties are taken into account: aerodynamic parameters, thrust curve, initial conditions and IMU errors. The Monte Carlo approach was used for simulations and Circular Error Probable was used as a measure of dispersion. Generic rocket mathematical and simulation model was created in MATLAB/Simulink 2020b environment. Results show that the use of control algorithms greatly reduces the impact point dispersion.
Results show that the use of control algorithms greatly reduces the impact point dispersion. flight simulation dispersion analysis rocket pulse jet control pmc-status-qastatus 0 pmc-status-live yes pmc-status-embargo no pmc-status-released yes pmc-prop-open-access yes pmc-prop-olf no pmc-prop-manuscript no pmc-prop-legally-suppressed no pmc-prop-has-pdf yes pmc-prop-has-supplement no pmc-prop-pdf-only no pmc-prop-suppress-copyright no
Monte Carlo analysis of the impact point dispersion due to the missile parameters and atmospheric conditions’ uncertainties was performed in [ 22 ] and the impact point dispersion reduction due to high spin motion was analyzed in [ 23 ]. In this paper, the analysis of the impact point dispersion caused by model uncertainties is presented. The uncertainties in the aerodynamic parameters, thrust curve, and initial conditions, as well as the uncertainties caused by the Inertial Measurement Unit model and its errors are analyzed. Two types of control algorithms were tested, Multi-Condition Control Algorithm (MCCA) and modified Proportional Navigation Guidance (mPNG).
The analysis was performed using the Monte Carlo approach. The prepared article is organised as follows: in Section 2 the mathematical model of the rocket is presented in the Section 2.1 with used assumptions and coordinate systems. The dynamic equations of motion, followed by additional kinematic equations are shown in that section. The external loads comprised of aerodynamics, gravity, propulsion, and correction thrusters are presented, and this is followed by the description of inertial parameters, atmosphere, and Inertial Measurement Unit modelling approach. At last, the used control algorithms are shown.
Mathematical Model 2.1.1. Assumptions For creating a mathematical and simulational model of a generic rocket, several assumptions were made. The rocket is modelled as a rigid body with six degrees of freedom and variable inertial parameters. It is controlled by a set of solid rocket motor thrusters, which use does not change the inertial and aerodynamic parameters of the rocket. Atmosphere model is taken from the International Standard Atmosphere [ 24 ]. Earth rotation and eccentricity are not modelled, the gravitational acceleration is constant and consistent with WGS-84 model [ 25 ].
The mathematical model includes the Inertial Measurement Unit (IMU) comprised of accelerometers and gyroscopes triades, modelled as second-order dynamical systems, with their disturbances that include noise, bias, scale factor and cross coupling as well as g-dependent factor for gyroscopes. 2.1.2. Coordinate Systems The coordinate systems used are presented in Figure 1 : The navigational coordinate system O n x n y n z n is a right-handed, Cartesian coordinate system fixed to earth. Its origin is located at any point and the O n x n y n plane is tangent to the surface of the earth.
The aerodynamic interference effects of the thrusters with the external flow were also omitted. 2.1.10. Inertial Parameters The instantaneous mass of the rocket is given as: (43) m ( t ) = m 0 − m p I c ∫ t 0 t F p ( t ) d t where m 0 is the starting mass of the rocket at time t 0 , m p is the mass of the propellant and I c is the total impulse given as: (44) I c = ∫ t 0 t k F p ( t ) d t where t k is the time of propellant burnout.
Inertial Measurement Unit Model It was assumed that the rocket’s is equipped with the strapdown Inertial Measurement Unit with the three-axis accelerometer and three-axis gyroscope, and these are the only sources of information about rocket position, velocity and orientation. Abovementioned design requirements are quite difficult to fullfill due to errors. Pure inertial navigation has a tendency due to drift. These drift errors might be reduced using integration with GPS receivers. Also, additional sensors like might be used to improve the system acccuracy. Magnetometers measurement are imprecise because the projectile and launcher structure are made from steel alloys.
High measurement range for X axis results from acceleration caused by main motor. This device requires supply voltage of 5 V. The IMU might be connected with the central onboard computer using military standard RS-422 serial interface. The maximum rate of data transmission for control purposes is 600 Hz. This measurement device is placed in front of the missile center of mass (between main motor unit and lateral thrusters module). Accelerometers model The acceleration of the rocket’s center of mass in O b x b y b z b coordinate system is: (50) a = a x a y a z = F b m In the general case, the accelerometer position need not to coincide with the center of mass of the rocket.
2.2. Simulation Model The mathematical model described in Section 2.1 was implemented in MATLAB/ Simulink 2020b environment. The main Simulink block model of the system is presented in Figure 4 . The program simulates the flight of the gasodynamically controlled rocket, calculates the loads from gravity, aerodynamics, thrust, and correction thrusters. It solves the set of ordinary differential equations for the rigid body with 6 degrees of freedom and variable mass. It includes the models of International Standard Atmosphere and Inertial Measurement Unit as well as the inertial navigation equation for determining the rocket’s position, orientation, and velocity.
Recent demand from the small satellite community has led to the development of a new series of star trackers that are specifically designed for small satellites. These units represent substantial improvements in mass, power consumption and cost over traditional star trackers, but suffer slightly in terms of accuracy and availability performance. The primary factors inhibiting their performance are the use of significantly smaller optics, and commercial off the shelf components (COTS). This thesis presents a series of strategies for improving the performance of small satellite star trackers (SSSTs). These goals are realized through the development of offline calibration procedures, flight software, validation tests, and optical trade studies to guide future development.
This thesis begins with the development of a target-based focusing procedure that enables precision control over the focus of the sensor optics. This improves the detection performance for dim stars, and ultimately increases the availability of the attitude solution. Flight software is developed to compensate for the effects of electronic rolling shutters, which reside on most COTS image detectors. Combined with a developed camera calibration procedure, these tools reduce the uncertainty with which a star tracker can measure the direction vectors to stars in view, ultimately increasing sensor accuracy. Integrated tests are performed to validate detection performance in dynamic conditions. These tests specifically examine the effect of slew rate on star tracker detection, and availability performance. Lastly, this thesis presents a series of optical trades studies that seek to identify design requirements for high performance SSSTs. The trends in availability and accuracy performance are examined as a function of different lens/detector configurations as well dual/triple-head sensor configurations.
Together, these strategies represent tools that aim to improve small satellite star tracker performance and guide future sensor development.
Recent demand from the small satellite community has led to the development of a new series of star trackers that are specifically designed for small satellites. These units represent substantial improvements in mass, power consumption and cost over traditional star trackers, but suffer slightly in terms of accuracy and availability performance. The primary factors inhibiting their performance are the use of significantly smaller optics, and commercial off the shelf components (COTS). This thesis presents a series of strategies for improving the performance of small satellite star trackers (SSSTs). These goals are realized through the development of offline calibration procedures, flight software, validation tests, and optical trade studies to guide future development. This thesis begins with the development of a target-based focusing procedure that enables precision control over the focus of the sensor optics. This improves the detection performance for dim stars, and ultimately increases the availability of the attitude solution. Flight software is developed to compensate for the effects of electronic rolling shutters, which reside on most COTS image detectors. Combined with a developed camera calibration procedure, these tools reduce the uncertainty with which a star tracker can measure the direction vectors to stars in view, ultimately increasing sensor accuracy. Integrated tests are performed to validate detection performance in dynamic conditions. These tests specifically examine the effect of slew rate on star tracker detection, and availability performance. Lastly, this thesis presents a series of optical trades studies that seek to identify design requirements for high performance SSSTs. The trends in availability and accuracy performance are examined as a function of different lens/detector configurations as well dual/triple-head sensor configurations. Together, these strategies represent tools that aim to improve small satellite star tracker performance and guide future sensor development.
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