ISRO's Reusable Launch Vehicles

Prashant12

Senior Member
Joined
Aug 9, 2014
Messages
3,027
Likes
15,002
Country flag
Isro readies its Swadeshi space shuttle

The onboard computer will help the RLV to glide for some distance before touching down like an aircraft, scientists at Isro told Deccan Chronicle.



The Reusable Launch Vehicle (RLV), for the first time, will be tested on land — the 2.2 km runway at ATR to be precise — with its under carriage in position after a freefall from a helicopter flying at an altitude of three km.

Bengaluru: For a change, Indian space scientists will soon move from the east coast — Satish Dhawan Space Centre (SDSC), Sriharikota Range — to the mainland to track the flight and landing of swadeshi version of the space shuttle at the Aeronautical Test Range in the ‘Science City’ at Challakere in Chitradurga district.

The Reusable Launch Vehicle (RLV), for the first time, will be tested on land — the 2.2 km runway at ATR to be precise — with its under carriage in position after a freefall from a helicopter flying at an altitude of three km. The onboard computer will help the RLV to glide for some distance before touching down like an aircraft, scientists at Isro told Deccan Chronicle.

While the RLV has been designed to test a wide spectrum of technologies considered critical for the human space flight programme (December 2021), it will also help Isro realise the concept of Two-stage-to-orbit (TSTO), the space agency’s novel attempt to reduce the cost of launch of satellites by a factor of ten.

https://www.deccanchronicle.com/science/science/161019/isro-readies-its-swadeshi-space-shuttle.html
 

fire starter

Tihar Jail
Banned
Joined
Jan 14, 2020
Messages
9,609
Likes
84,137
Country flag
word-image-5.png

As part of the Reusable Launch Vehicle Technology Demonstration (RLV-TD) program, the Indian Space Research Organization (ISRO) has been developing various technologies that will serve as building blocks for a future Two-stage-to-orbit (TSTO) reusable launch vehicle. These technologies are being developed in phases through a series of experimental flights.
Flush Air Data System (FADS)
Flight control systems require accurate real-time data such as angle of attack, angle of sideslip, dynamic pressure, Mach number and free stream static pressure. Flight management including managing thermal and aeromechanical loads as well as trajectory and flight path is performed based on accurate vehicle data. Flush air data system (FADS), as the name implies, measures data from orifices flush with the surface of the nose cone and hence there are no devices protruding from the body of the vehicle. FADS of the configuration shown in Fig.1 below was developed and flight-tested during the Hypersonic Flight Experiment (HEX) successfully conducted on May 23, 2016. The FADS was restricted to monitoring mode to validate its performance and will be used for guidance in the subsequent flights.

FADS is generally used for gathering data below altitudes of 35-40 Km. Above this, flight control is driven by data from inertial navigational systems(INS). INS accuracy below these altitudes are reduced due to wind and other atmospheric effects. For instance, autopilot governing parameters such as angle of attack (AoA) and side-slip angle are some of the key ones affected. The guidance and control system demand very high accuracy of air data. These are important for gain scheduling and switching over controls from reaction control system (RCS) to aerodynamic control surfaces.

The pressure ports are arranged in a crucifix pattern with five in the vertical meridian and four in the horizontal meridian. Two horizontal ports are provided on either side of the vertical meridian. A configuration of nine ports was selected to provide adequate redundancy and to facilitate computation of air data parameters even after failure of a pressure sensor, or blockage of a pressure port.

Extensive wind-tunnel tests were carried out to benchmark and prove the FADS. Subsonic tests were carried out at the National Wind Tunnel Facility at IIT Kanpur and higher Mach number tests at CSIR-NAL, Bengaluru. The FADS computed data during 10s to 70s during ascent phase and below 20 Km altitude during descent phase of the HEX. Data computed was found to be within the designated accuracy targets.
word-image.png

Navigation, Guidance and Control Systems (NGC)
word-image-scaled.jpeg

Navigation system

The configuration of the navigation system is decided by the accuracy requirement during the landing phase. Position accuracy of 50 m along runway and 5 m across runway is required for carrying out an autonomous landing. During landing the altitude accuracy requirement is 1 m and velocity accuracy requirement is 0.5 m/s. These requirements cannot be met by stand-alone INS. Hence global positioning system (GPS) aided navigation system (GAINS), which provides position and altitude accuracy of 50 m and velocity accuracy of 0.5 m/s is used. In addition, radar altimeter (RA) enhances the altitude accuracy to 1 m during landing.

INS for RLV-TD: This system consists of the following: Three gyros are mounted in the ortho-skewed configuration (each gyro mounted in pitch/yaw/roll orthogonal axis and two accelerometers in roll–yaw plane of the vehicle, which give fail-operational redundancy for acceleration measurements in yaw and roll axes. The navigation software residing in the on-board computer processes the data from inertial sensors to generate functional parameters for closed-loop guidance (CLG) and control. It computes body rates and quaternions; position,velocity and altitude; inertial velocity and acceleration and air data parameters.

GPS-aided inertial navigation system: GAINS is used to improve the navigation accuracy. GAINS computer is interfaced to GPS receiver and Mission management computer (MMC). Kalman filter-based error estimation is carried out to estimate the velocity and position error. The navigation software in MMC uses the error estimates to correct the velocity and position data in a feed-forward manner.

Altitude estimation using aided INS and RA data: During the landing phase, the RA data are used to estimate the error in navigation altitude. The estimated error is used to correct the navigation altitude to meet landing accuracy.

Ceramic servo accelerometer package: During the descent phase of the flight, where wind effects are prominent and estimation of air data parameters is less accurate, Ceramic Servo Accelerometer Package (CSAP) is used to generate acceleration data for control. It consists of six ceramic servo accelerometers mounted in skewed triad–hexad geometry (six accelerometers, 60° apart on the planar surface of a cone with half-cone angle 54.736°) along with processing electronics. The measurement range of the system is ±20 g in coarse range. To meet the resolution requirements of the mission (HEX), the measurement range is switched from coarse (±20 g) to fine range (±4 g) at booster burnout. The data from CSAP are processed in MMC to generate lateral acceleration (Ny, Nz). The resolution is 3.5 mg and 2.8 mg in yaw and pitch axis respectively.
word-image-1-scaled.jpeg

Guidance system
The Closed Loop Guidance (CLG) system steers the vehicle to the desired landing point, meeting constraints such as horizontal and vertical velocity at touchdown
word-image-1.png


Approach and landing phase
In this phase, the CLG commands (normal acceleration and bank angle) are provided to steer the vehicle to a desired landing point. This is selected on-line, based on the energy available. The approach and landing phase guidance includes an on-line trajectory design and a path controller to track the planned trajectory. The entire approach and landing phase trajectory is generated on-board at the start of this phase. The trajectory is divided into vertical and horizontal planes. The vertical dynamics is controlled by commanding normal acceleration (NZC) and the horizontal dynamics is controlled by bank angle (σC) command. The guidance problem is formulated by assuming that the vertical dynamics is decoupled from horizontal dynamics. The algorithm features include: (i) Retargetting: on-line selection of landing point based on the range to be covered. (ii) Safe mode guidance: for extreme performance variations. (iii) Dynamic normal acceleration command limit: to steer the vehicle to fly in the safe angle of attack envelop. The CLG steers the vehicle to the desired landing point, meeting constraints such as horizontal and vertical velocity at touchdown.
word-image-2.png

Descent phase
In the descent phase, pitch and roll control is achieved by two elevons and yaw by two rudders. During the high angle of attack regime, rudder is not effective and yaw control is achieved by RCS. Once angle of attack reduces, a rudder become effective and thereafter is used for yaw control. RCS is provided as back-up for pitch, yaw and roll control. The aerodynamic angles (α, β, σ) are controlled till Mach number 2. Lateral acceleration (Nz, Ny) and bank angle (σ) are also controlled below Mach number 2. In conventional launch vehicles, pitch, yaw and roll plane dynamics is decoupled, whereas in RLV it is highly coupled and hence multi input multi output (MIMO) design is used. To take care of trajectory variations in control design, 2D gain scheduling based on Mach number–dynamic pressure is used. Aerodynamic control starts after booster separation.

Descent phase is divided into three sub-phases

Phase 1: This phase starts after booster separation and includes TDV coasting and reorientation. Here elevons are used to control pitch and roll dynamics, and RCS is used to control yaw dynamics. At the end of reorientation, the vehicle starts descending at a high angle of attack. Time-based gain scheduling is adopted during this phase. As the angle of attack reduces, rudder effectiveness improves.

Phase 2: Once the rudder becomes effective (comes out of the shadow of the fuselage), it is used for active yaw control. TDV is completely controlled using aerodynamic control surfaces and RCS is used in backup mode. MIMO design is carried out for the stabilization of coupled yaw– roll dynamics. Two-dimensional gain scheduling based on Mach number versus dynamic pressure is used.

Phase 3: This phase starts when Mach number reduces below 2 and altitude below 20 km. During this phase, wind velocities significantly influence the estimation of aerodynamic angles. So, in place of aerodynamic angles, accelerations are sensed and commanded by guidance for attitude control. Pitch plane design is done as in a conventional launch vehicle. MIMO design is carried out for stabilization of coupled yaw–roll dynamics. Gain scheduling is based on Mach number vs dynamic pressure.

Trim requirement and its scheduling: TDV is intended to follow a defined angle of attack trajectory based on Mach number and hence there is a known requirement of control surface deflection (trim control requirement). Since this Mach versus angle of attack profile is non-monotonic, 2-D trim schedule is adopted in all the three phases.

NGC system configuration The overall NGC system includes MMC, which computes the navigation information from the sensor data and generates steering, control and sequencing commands. The control commands are routed through the stage processing system to the actuators through the control electronics package. NGC is configured as a dual redundant cross-strapped system to handle subsystem failures. MILStandard 1553B bus is used for communication between MMC and other elements in the NGC system. The performance of the subsystem is assessed from the telemetry data acquired through the integrated data acquisition and processing systems. The 1553B communication bus utilization is also double compared to the existing launch vehicles, due to the presence of increased number of subsystems. Integrated simulation facility was designed and established to meet the validation requirements of the NGC systems of RLV-TD, and enabled the performance assessments of the system, including software and final initialization of data leading to the clearance for flight. Digital simulations were carried out to finalize the vehicle, mission design and validate the on-board algorithms. On-board software including navigation, guidance, control and other subsystems software embedded in the actual flight hardware were thoroughly validated in the integrated configuration using processor in loop simulation test bed.

HLS tests ensured that the INS and navigation software provided designed performance for the mission under nominal conditions as well as sensor isolation conditions. The repeatability, drift characteristics and performance of inertial sensors were critically evaluated across days and found acceptable. Through ALS simulations in Iron Bird, actuator performance was assessed in closed loop environment with vehicle dynamics, for different flight conditions. This ensured adequacy of end-to-end control performance
 

Indx TechStyle

Kitty mod
Mod
Joined
Apr 29, 2015
Messages
18,240
Likes
55,879
Country flag

Okabe Rintarou

Senior Member
Joined
Apr 23, 2018
Messages
2,337
Likes
11,986
Country flag
Quoting above tweet from Delhi Defence Review.
WTF? They are planning to recover S200? What's the point in recovering a solid stage? Maybe he mistakenly said 1st and 2nd stage when he actually meant L110 and C25 (I know L110 is not ground lit)?
 

Indx TechStyle

Kitty mod
Mod
Joined
Apr 29, 2015
Messages
18,240
Likes
55,879
Country flag
Key landing test will push reusable vehicle RLV-TD closer to Orbital Re-Entry mission

Isro's reusable launch vehicle-technology demonstrator.
BENGALURU: Isro, which has been making quiet progress on the reusable launch vehicle-technology demonstrator (RLV-TD) is looking to carry out a key landing Experiment — RLV-LEX — in the next few months that will push it closer to an orbital re-entry experiment (ORE). The planned landing experiment will be carried out in Challakere in Chitradurga district, some 220km from Bengaluru.
Isro chairman S Somanath, while confirming that the agency has planned the RLV-LEX this year, said: “...We will be demonstrating one of the critical technologies — the approach and autonomous landing on a runway. This will happen in Challakere. We are preparing for the test and systems are being readied. We will soon make an announcement.”
In the LEX, the vehicle will be carried using a helicopter to an altitude of about 3km to 5 km and released at a distance of approximately 4km to 5km ahead of the runway with a horizontal velocity. As per Isro, after the release, the RLV glides, navigates towards the runway and carries out a conventional autonomous landing with a landing gear.
S Unnikrishnan Nair, director, Vikram Sarabhai Space Centre (VSSC), said: “We are planning for the test in the next three to four months, the hardware is nearly ready. The RLV will be released from the helicopter under controlled conditions. It will have various control systems, including its own navigation and guidance control systems and aerodynamics sensors etc. This experiment will simulate the last 800m to 1km of the actual orbital mission.”
Pointing out how landing is among the most complex activities in any mission, Nair said the RLV-LEX would take the technology demonstration one step closer to the planned ORE.
“Once we successfully complete this mission and we have validated the software, landing gear and get data on how the aerodynamics sensors worked to manoeuvre the aircraft and bring it back to the intended spot on the runway and other critical technologies, we will be ready for the orbital re-entry experiment. For this the RLV will be scaled up,” Nair said.
As per Isro, in ORE, a wing body called Orbital Re-entry vehicle (ORV) will be taken to an orbit by an ascent vehicle derived from the existing GSLV and PSLV stages and stay in orbit for a stipulated period, re-enter and land in a runway autonomously with a landing gear.
“Before the RLV-LEX we’d done the RLV-TD HEX-01 (hypersonic experiment) mission in which we successfully validated autonomous navigation, guidance & control, reusable thermal protection system and re-entry mission management. Once LEX is done, we’ll need to integrate both for the ORE,” Nair said.
Carried out on May 23, 2016, the RLV-TD HEX was a 770-second suborbital flight and designed to land on sea. The experimental mission saw the HS9 solid rocket booster carrying RLV-TD to a height of about 65km from where the vehicle began its descent followed by atmospheric re-entry at around Mach 5 (five times the speed of sound).
Isro, which has been working on this technology for more than a decade, decided to develop it primarily to address the cost and time issues. “The cost of access to space is the major deterrent in space exploration and space utilisation. A reusable launch vehicle is the unanimous solution to achieve low cost, reliable and on-demand space access,” Isro has said.
However, mastering this technology will provide multiple other benefits, including in development of different types of launch vehicles, space transportation and so on. While the ORE will be a major milestone, the RLV-TD is only a technology demonstrator and the development of an actual re-usable launch vehicle will take more time.
 

Mikesingh

Professional
Joined
Sep 7, 2015
Messages
7,353
Likes
30,450
Country flag
Two Stage To Orbit( TSTO) concept based on RLV. Here RLV is used as the first stage. Rocket can be recovered. RLV lands like Aircraft. Reusable Rocket underdevelopment.

Image
1660311127515.png
1660311174880.png

Courtesy:
Varun Karthikeyan
 

karn

Senior Member
Joined
Apr 17, 2014
Messages
3,603
Likes
15,360
Country flag
Two Stage To Orbit( TSTO) concept based on RLV. Here RLV is used as the first stage. Rocket can be recovered. RLV lands like Aircraft. Reusable Rocket underdevelopment.

Image
View attachment 167383
View attachment 167384
[URL='https://twitter.com/Varun55484761']Courtesy:
Varun Karthikeyan[/URL]

I remember seeing line drawings of this . Brilliant concept, very efficient.
But isn't the RLV also in development? Only subscale has been fabricated right with no runway landing proven yet
 

Mikesingh

Professional
Joined
Sep 7, 2015
Messages
7,353
Likes
30,450
Country flag
I remember seeing line drawings of this . Brilliant concept, very efficient.
But isn't the RLV also in development? Only subscale has been fabricated right with no runway landing proven yet
Right! It's under development. Let's hope they get it done by next year.
 

Latest Replies

Global Defence

New threads

Articles

Top