ANUBIS. Payload User Guide Version 1.0 March 8 th, 2019

Transcription

1 ANUBIS Payload User Guide Version 1.0 March 8 th, 2019

2 Suborbitality Version: 1.0 Created Revised Approved Project: Suborbital Launch Vehicle(ANUBIS) 18/02/ /03/ /03/2019 Document type: Payload User Guide HG DH HG Revision History: Version Date Author Affiliation Chapters Updates /03/2019 HG&DH&MG Suborbitality All Document creation. Cleared for public release Version 1.0 Cleared for Public Release 2

3 TABLE OF CONTENTS Acronyms Introduction Company Description Development Purpose Business overview Launch Vehicle ANUBIS Overview Subsystems Propulsion Module Recovery Module Payload Modules Control and Guidance Systems Avionics & Instrumentation Structure Facilities Headquarters Launch Operator Launch site Mission Suborbital Flight Profile Launch Campaign Timeline Flight Post Flight Payload Interfaces Mechanical Interface Custom Mounting Plates Payload Access Doors Payload Options Electrical Interface Communication Environment Atmospheric Conditions Thermal Conditions Mechanical Loads Version 1.0 Cleared for Public Release 3

4 5.6 Reporting & Documentation Payload Integration Integration Documentation Shipping Testing Vacuum Thermal Vibration Prelaunch Integration Payload accessibility Contact References List of Figures List of Tables ACRONYMS ADCS CGT ESC FTS MECO MSL PSM RCS TRL FTS Attitude Determination and Control System Cold Gas Thruster Esrange Space Center Flight Termination System Main Engine Cut-Off Mean Sea Level Payload Servicing Module Reaction Control System Technology Readiness Level Flight Termination System Version 1.0 Cleared for Public Release 4

5 1 INTRODUCTION ANUBIS is designed with the single goal to make access to space affordable for everyone. With a proven, reliable, and efficient solid rocket propulsion system alongside modern, strong, and lightweight materials, and inexpensive but dependable off-the-shelf hardware, ANUBIS will utilize a unique, game-changing methodology, combining the simplicity and heritage of various flight proven space concepts. Working with industry and educational partners, the service will be designed to suit the needs of all types of customers, with a focus on reliability, safety, and keeping the price per kilogram payload competitive on the world stage. 1.1 COMPANY DESCRIPTION Suborbitality is a European New Space company with a mission to be engaged in the global market for space systems by introducing low-cost launch services to suborbital space. Suborbitality is utilizing space industry-proven technologies and a lean business model to create the world s only suborbital rocket specifically tailored to provide a low-cost, smart, reusable, and reliable solution to a market stagnating under high prices and low launch availability. 1.2 DEVELOPMENT PURPOSE Access to the upper layers of the atmosphere from km, at the edge of space is currently very limited. Such a wide range can t be addressed by high altitude balloons and is secondary, if considered at all, for all current active space launch vehicles which are dedicated for much higher altitudes. Developing ANUBIS as a cost-effective launch vehicle will fill a gap in the space market allowing more scientific research, space component verification experiments, exo-atmospheric and astronomical research, weather monitoring, and short duration microgravity experiments. 1.3 BUSINESS OVERVIEW ANUBIS, the flagship of Suborbitality, is a vehicle to provide a suborbital launch service to the markets of Basic and Applied Research, Aerospace Hardware Testing and Demonstration, Education, and Media, Public Relations, Novelties, and Memorabilia. In order to provide for these markets and open them up to researchers, students, organizations, and developing countries that have been previously restricted due to price, Suborbitality is focused on providing suborbital launches as frequently and efficiently as possible, at the lowest possible cost. Customer service and accessibility will always be a number one priority. Version 1.0 Cleared for Public Release 5

6 2 LAUNCH VEHICLE 2.1 ANUBIS OVERVIEW Function Manufacturer Suborbital launch vehicle Suborbitality Height 7.5 m Diameter 0.4 m Dry mass 175 kg Wet mass 355 kg Stages 1 Payload kg Propulsion system Fuel Solid rocket motor Composite propellant Flight control Spin stabilized Spin control Yo-yo despin mechanism ADCS &RCS Cold Gas Thrusters Recovery system Dual deployment Recovery control Controlled parachute Primary launch site Esrange Space Centre Table 1. ANUBIS overview and specifications. Version 1.0 Cleared for Public Release 6

7 2.2 SUBSYSTEMS ANUBIS is divided in 7 main subsystems, which are independent of the mission or specific payload: 1 Propulsion Module 2 Recovery Module 3 Payload Modules 4 Communication Module 5 Control and Guidance Systems 6 Avionics & instrumentation Module 7 Airframe Table 2. List of ANUBIS subsystems Propulsion Module The rocket will be powered with a single-use solid rocket motor, Ra. This motor is developed specifically to suit ANUBIS as it offers a long, stable burn allowing the payload to experience as low as possible accelerations while maintaining the safety margins of the flight. The Ra motor is qualified for flight after a set of lab-development tests, followed by complete firings of the motor in various conditions simulating all the expected flight scenarios. The motor qualification testing campaign data is available for customers and the public to check and review. Ra demonstrates an excellence in design and illustrates the capabilities of the propulsion research and development team at Suborbitality Recovery Module ANUBIS uses a low-shock magnetic-spring separation system to split the rocket and deploy a ballute, a parachute-like device used for slowing the rocket down from high altitudes and supersonic speeds. At a lower altitude, once subsonic speeds have been achieved, a GPS-guided parafoil will be deployed and deliver both halves of ANUBIS to a desired landing &recovery location near the launch site Payload Modules Coming in multiple lengths, aluminum-capped carbon fiber pods will be supplied to the customer for payload assembly. Each pod can be customized with options including space-access, space- Version 1.0 Cleared for Public Release 7

8 insertion, space-ejection, or a simple stationary door, either air-tight, or pressure-balanced. Power, data, and communication will be supplied, with camera or other monitoring options available. Payloads will be shipped in their modules to ESC to be integrated onto ANUBIS. Details on dimensions, mounting, servicing, integration, and environmental conditions can be found in sections 5 and Control and Guidance Systems Controlling the rocket starts from the de-spin maneuver to stop the passive spin stabilization assuring the stable ascent of the rocket. After the spin has been reduced to only a few rotations per minute, the reaction control system (RCS) will be activated in the form of cold gas thrusters (CGT), which will control the orientation of the rocket in space. Payloads with special astronomical needs such as sun and star gazing applications will have access to the usage of the RCS of ANUBIS to perform their experiments in space. For microgravity experiments, the RCS will remove all rotation from the rocket, allowing for an excellent quality of microgravity. Also, the system will orient the rocket to its correct position, prior to the recovery system deployment Avionics & Instrumentation The Avionics & Instrumentation module on board ANUBIS controls all rocket functions and maneuvers during the flight and decent. It is also responsible for establishing communication between the ground station and rocket at all times. These subsystems have control of the flight trajectory and de-spin events, and are directly connected to the payload servicing modules, as they are responsible for delivering the power necessary for operation, communication, data handling, and command. The module contains batteries that supply power to the whole rocket and the payload servicing modules. It is also equipped with a power distribution system that maintains an efficient and optimum usage of the power available. The avionics and instruments of ANUBIS are developed following proven technologies with a long spaceflight heritage and an optimized innovative design to accommodate and serve all the sizes and type of suborbital experiments in the market in terms of power supply, communication, and data handling and storage Structure The rocket structure is designed to handle the loads of launching into space as well as loads of hitting the atmosphere during re-entry and landing. ANUBIS is primarily manufactured from extremely strong and ultra-light carbon composite layups. This contributes to decreasing the overall mass of the rocket dramatically while maintaining high levels of strength allowing the rocket to optimize its flight parameters in terms of fuel consumption. The internal structure of the rocket is made of various materials depending on the loads each component withstands. However, a majority of the internal structure, ribs, bulkheads and Version 1.0 Cleared for Public Release 8

9 connections are made of aerospace-grade aluminum alloys to allow for strong but lightweight interfaces that allow for simple assembly and reliability over repeated use. 3 FACILITIES 3.1 HEADQUARTERS The headquarters and engineering office of Suborbitality, where all the design and operation planning takes place, is located at Palace Adria, Jungmannova 31, entrance A, 3rd floor Prague, Czech Republic. Our engineering team is based in our headquarters with direct active contacts to more than a dozen of partners working on the manufacturing, testing, and research & development of ANUBIS. Fig. 1. PalaceAdria in Prague, Czech Republic 3.2 LAUNCH OPERATOR Suborbitality is cooperating with the Swedish Space Corporation (SSC) for the launch campaign of ANUBIS. The usage of the facilities at Esrange Space Center (ESC) for final assembly and safety qualification, and the launch pad for launching the rocket is conducted under an agreement between Suborbitality and SSC; customers are not involved in this process. 3.3 LAUNCH SITE Esrange space center ESC is located in the north of Sweden (68 N, 21 E). The facilities are used by international scientific community for launching sounding rockets for microgravity and atmospheric research. Esrange as well has one of the world s largest civilian satellite ground stations. The main building at Esrange hosts the technical facilities such as: Safety center Operations center Version 1.0 Cleared for Public Release 9

10 TM center The rocket launch area lies only 1 km away from the main building. This is the main area where assembly of payloads takes place prior to flights. The impact area at Esrange is a 120 km long and 75 km wide large diamond shaped area up north of the launch pad. This area is uninhabited which makes it an ideal choice for ejecting payloads from the rocket as well as a landing zone for the rocket. Fig. 2. Downrange impact zones at Esrange Space Center Version 1.0 Cleared for Public Release 10

11 4 MISSION 4.1 SUBORBITAL FLIGHT PROFILE A Suborbital flight from Earth, by its definition reaches outer space (the internationally accepted Kármán line at 100 km), but will intersect the atmosphere and the ground before completing a complete revolution (orbit). A flight onboard ANUBIS will launch at a slight angle off of vertical (88 ), with the target of reaching an altitude between 120 and 225 km, depending on the total mass of payload carried, providing space conditions, and between 3 and 5 minutes of microgravity, before returning in one piece to the ground with a guided parachute. Fig. 3. Standard flight profile for ANUBIS with 120 km apogee. Version 1.0 Cleared for Public Release 11

12 4.2 LAUNCH CAMPAIGN TIMELINE Kick-off Project kick-off meeting. Launch agreement signed T-3 months Payload Servicing Module sent to customer for payload assembly (if required) T-6 weeks Payload sent to Suborbitality (Assembled to the PSM or not if otherwise agreed) T-3 weeks Inspection of payloads. Assembly of the payloads start T-6 days Final chance for flight requirements adjustment T-3 days Final recovery instructions T-2 days Countdown procedure available T-1 day Final minor payload changes T+1 day Post-flight data transfer to customer T+1 week Post-flight official review T+2 weeks Payload delivery back to customer (If not requested otherwise) T+1 month Flight Report published Table 3. Launch campaign timeline Version 1.0 Cleared for Public Release 12

13 4.3 FLIGHT Event Time (s) Approx. altitude MSL (km) Engine ignition T+0 0 Max Q. T Engine shut down T Apogee T Re-entry control start T Ballute deploy T Main chute deploy T Touchdown T+> Table 4. List of approximated nominal flight events. 4.4 POST FLIGHT Immediately after touchdown, the recovery team at ESC will be dispatched to bring the entire rocket back to the launch facilities. After visual inspectionand flight assessment, PSMs will be disassembled from the rocket, data will be downloaded, and payloads will be processed according to customer specifications. Version 1.0 Cleared for Public Release 13

14 5 PAYLOAD INTERFACES As ANUBIS is mainly a suborbital servicing vehicle, its main mission is to deliver its payload into the designated altitude. This has pushed our design team to offer different payload servicing modules (PSM) to cover majority of the market needs. Fig. 4.Rendered CAD model of the PSM different versions available for customers. Specifications PSM-1 PSM-2 PSM-3 PSM-4 Usable Height (mm) Usable Diameter (mm) Max. Payload Mass (kg) No. of access doors Large Access Hatch Access to Space Option No Yes Yes Yes Ejection to Space Option No Yes Yes Yes Table 5. Payload Servicing Modules Specifications Version 1.0 Cleared for Public Release 14

15 Assembly of payloads inside the PSM can be done in-house by Suborbitality prior to the launch campaign or can be done directly by the customer. In case of the latter, the desired PSM will be provided to the customer to attach the payload and will be sent back to Suborbitality for integration before flight. Payloads can be attached to a standard grid pattern, the custom mounting plates, or a customized bulkhead based on customer needs. Options for pressurization, space access, space insertion, or space ejection are available. A completely customized payload servicing module option is available as well and includes the same general interface as the conventional PSMs, with the same available options. 5.1 MECHANICAL INTERFACE Each payload bay module s lower plate contains an isometric pattern of M6-tapped holes, with the spacing show in figure 5. The usable diameter of the payload bay is 330 mm, with the heights specified per payload servicing module specified in table 4. Post-integration access is achieved by small access panels on each payload module. Dimensions are provided in figure 7. An installed custom mounting plate is shown, details of which are covered in the next section. Fig. 5. Mounting pattern for static payload modules. Version 1.0 Cleared for Public Release 15

16 5.1.1 Custom Mounting Plates For increased payload mounting flexibility, 4 mm thick triangular mounting plates will be provided which the customer can freely modify to suit their mounting needs. Typically, 10 will be provided with the payload module for the customer to use, but customers must be aware that each plate contributes to the total booked payload mass. Each plate has a mass of 24 grams. All unused plates should be returned to Suborbitality. Dimensions for modification are shown in Figure 6, which must be kept within the usable boundary area. There is a 4 mm gap behind the custom mounting plates, where screws may protrude, if necessary. Fig. 6. Custom mounting plates provided for customer modification. Version 1.0 Cleared for Public Release 16

17 5.1.2 Payload Access Doors In order to allow easy access to payload power, data, and communication post-integration, before launch, access doors have been provided on each payload servicing module. The numbers of which are specified in Table 4, and the dimension of the doors is shown below in Figure 7. Fig. 7. Payload Access door dimensions and position. Version 1.0 Cleared for Public Release 17

18 5.2 PAYLOAD OPTIONS In their standard configuration, payload servicing modules are pressure balanced and statically attached to the supplied mounting plate. Purchasable options include: Airtight compartment, pressurized with nitrogen or other requested inert gas Actuated hatch for space access Actuated hatch + extendable bed for space insertion Actuated hatch + payload ejection system Custom length payload servicing modules Fig. 8. PM-2 with actuated hatch (hatch actuation may vary from this rendering). For the space insertion and payload ejection options, the following sizes apply: PM-1: (Option not available) PM-2: 3U wide x 2U high PM-3: 3U wide x 3U high PM-4: 3U wide x 5U high Please contact Suborbitality for option pricing, custom orders, or special requirements at: booking@suborbitality.com Version 1.0 Cleared for Public Release 18

19 5.3 ELECTRICAL INTERFACE Each PSM is powered externally through power cables attached to an implemented interface. Once the rocket is vertical and the final checks start prior to launch, the PSMs computers are powered directly from the rocket s main battery. This allows the payloads to receive power all the time needed for their operation/charge without the need of their removal from the rocket. The customers connect their payload to electric pins located inside each PSM. The type and location of the electric pin connectors are determined during the payload integration process. Suborbitality will provide the customers with several options of payload connector halves. However, customers, with specific connector requirements, will use their own payload connector halves and provide Suborbitality with the other PSM connector halves. 5.4 COMMUNICATION Each PSM receives real-time data from the launch vehicle sensors and flight computer and sends it to the payload via the communication interface. The customer can connect to the communication interface and have access to the vehicle status, flight phase, and sensor data. The beginning and end of each flight phase are reported in real-time so that the customers can monitor their payload in different flight conditions. The in-flight sensor data (location, attitude, and weather) are realtime streamed to the PSM communication interface. Version 1.0 Cleared for Public Release 19

20 5.5 ENVIRONMENT Atmospheric Conditions It is a customer option to have an individually sealed and pressurized PSM, and if required, climatecontrolled transportation, and storage, prior to integration. Otherwise, Figure 10 below shows the average temperature and humidity the payload could be subjected to during transport to ESC, or while on the launch pad prior to launch. Fig. 9. Simulated yearly conditions in Kiruna, Sweden: the location of Esrange Space Center Thermal Conditions During transport and preflight, payloads may be subjected to the thermal conditions relative to the seasonal weather at ESC in northern Sweden. Updated conditions will be collected prior to each flight and reported to the customers. The rocket thermal conditions during flights will be sent to each customer based on the rocket configuration. However, due to solar radiation outside of the atmosphere, the internal skin temperature of the payload compartments is expected to rise to approximately 45 C. Due to aerodynamic heating, the outer structure will reach more than 210 C which is expected to be the point of max heating during ascent, rather than during reentry (will be reported individually). Cooling of the PSM to a certain temperature is available upon request Mechanical Loads The largest accelerations will occur during engine firing prior to max Q. Maximum axial and radial accelerations, along with vibration estimation data will be provided to the customer during payload requirements discussions. 5.6 REPORTING & DOCUMENTATION Suborbitality will provide detailed reports to the customers in terms of servicing, documentation, live status updates, and flight performance data prior to flight. Version 1.0 Cleared for Public Release 20

21 6 PAYLOAD INTEGRATION 6.1 INTEGRATION To assure the highest level of engineering quality and optimize both time and money of our customers, integration of payloads is done either at the engineering office of Suborbitality in Prague or directly at the launch site prior to assembly and safety inspections of the spaceport authorities. The integration process and culture of Suborbitality allows the safety teams to work directly alongside our integration team. This increases the safety and quality of our missions and has a direct impact on the costs, as it decreases the launch campaign duration drastically. Payload integration will be done during the assembly of the launch vehicle at the spaceport. Propulsion module assembly comes last on the checklist, making accessing the payload bays possible even for a last-minute update or maintenance. 6.2 DOCUMENTATION Preliminary and critical payload reports will be prepared before each flight to guarantee the coherency and integrity of work between the customer and Suborbitality. Post flight documentation will be provided entirely by Suborbitality prior to flights. More details on the documentation requirements will be sent to each customer individually based on the nature of the mission. 6.3 SHIPPING Shipping costs of the PSM(s) to the customer and from the customer to Esrange Space Center will be calculated by the time of the launch agreement signing, and covered by the agreed-upon deposit received by the customer. If a customer will be shipping their payload separately, to be assembled to the PSM by the launch provider upon the flight, the customer should mail their packaged payload directly to Suborbitality s headquarters. Shipping arrangements will be done with each customer separately to guarantee the safety of the payload. Suborbitality headquarters address: Palace Adria, Jungmannova 31, entrance A, 3rd floor, Prague, Czech Republic 6.4 TESTING The payload should be subjected to qualification tests to ensure its compatibility and readability to be launched onboard ANUBIS. The tests in the scope of a nominal suborbital flight are: Vacuum Payloads should be tested in vacuum conditions to simulate the flight conditions; these tests shall guarantee the operability of the payloads prior to its integration on ANUBIS. Version 1.0 Cleared for Public Release 21

22 In case of lack of access (completely or partially) to experimental equipment to verify and test the payload to these measurements, contact Suborbitality sales department to organize such verification tests to be done by our team Thermal Thermal testing shall take place prior to each flight, as follows the thermal constraints for the launch of ANUBIS. Constraints: - Heating of the outer structure Do not heat up the outer structure more than 8 C above ambient temperature - Feed-Through Cable parts close or in contact to cable < 65 C - Heat Transport in the Module Interface parts facing other modules < 50 C - Convection between Modules air temperature at the module interface < 8 C above ambient temperature - Pre-Flight -Flight Integration area: 20 (± 5 C) Roll out: -30 to 20 (± 5 C) for 30 Minutes Launch pad: 17(± 8 C) Ascent: More than 210 C (Outer structure nominal) Reentry: TBD based on flight specific conditions -Post Flight Recovery: -30 to 20 (± 5 C) for 100 Minutes Vibration Vibration test is required before each flight. Vibration values differ based on each flight lift-off weight; data for this test will be sent directly to each customer upon flight assessment reviews are done. In case of lack of access (completely or partially) to experimental equipment to verify and test the payload to these measurements, contact Suborbitality sales department to organize such verification tests to be done by our team. Version 1.0 Cleared for Public Release 22

23 6.5 PRELAUNCH INTEGRATION Integration procedure takes place before the flight at the assembly designated areas specified at ESC. Integration is done based on cooperation between Suborbitality and ESC and is a smooth process that doesn t require customer physical presence. 6.6 PAYLOAD ACCESSIBILITY Due to the cooperation between Suborbitality and the spaceport safety teams and based on years of experience in the rocketry field, the smart design of utilizing flight proved concepts with strong operational heritage that increases the confidence in the launch vehicle and maintaining very high levels of safety prior, during and after launch, access to the payloads on the rocket is possible up to 90 minutes before launch. Version 1.0 Cleared for Public Release 23

24 7 CONTACT If you are considering reaching space with Suborbitality, please contact our sales department: Suborbitality s.r.o. Palace Adria, Jungmannova 31, entrance A, 3rd floor Prague, Czech Republic Tel: Version 1.0 Cleared for Public Release 24

25 8 REFERENCES 8.1 LIST OF FIGURES Fig. 1.Palace Adriain Prague, Czech Republic Fig. 2. Downrange impact zones at Esrange Space Center Fig. 3.Standard flight profile for ANUBIS with 120 km apogee. Fig. 4.Rendered CAD model of the PSM different versions available for customers. Fig. 5.Mounting pattern for static payload modules. Fig. 6. Custom mounting plates provided for customer modification. Fig. 7. Payload Access door dimensions and position. Fig. 8. PM-2 with actuated hatch (hatch actuation may vary from this rendering). Fig. 9. Simulated yearly conditions in Kiruna, Sweden: the location of Esrange Space Center. 8.2 LIST OF TABLES Table 1.ANUBIS overview and specifications. Table 2. List of ANUBIS subsystems Table 3. Launch campaign timeline Table 4. List of approximated nominal flight events. Table 5. Payload Servicing Modules Specifications Version 1.0 Cleared for Public Release 25