{"id":106170,"date":"2025-09-04T14:01:36","date_gmt":"2025-09-04T12:01:36","guid":{"rendered":"https:\/\/ilot.lukasiewicz.gov.pl\/offer\/design-services\/designing-of-the-missiles-systems\/rakiety\/"},"modified":"2025-12-09T16:09:05","modified_gmt":"2025-12-09T15:09:05","slug":"rockets","status":"publish","type":"page","link":"https:\/\/ilot.lukasiewicz.gov.pl\/en\/offer\/design-services\/designing-of-the-missiles-systems\/rockets\/","title":{"rendered":"Rockets"},"content":{"rendered":"\t\t
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Rockets<\/h1>\t\t\t\t<\/div>\n\t\t\t\t<\/div>\n\t\t\t\t
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With the ILR-33 BURSZTYN 2K rocket, a cost-effective, scalable and environmentally friendly design, we have the ability to efficiently experiment in microgravity and probe the atmosphere. The ILR-33 BURSZTYN 2K rocket is used during flight as a suborbital test platform, capable of providing up to 150 seconds of microgravity conditions for a 10 kg payload. The payload compartment can be adapted to the Customer\u2019s requirements, providing the best possible test conditions.<\/p>\n\n

ILR-33 BURSZTYN 2K<\/h3>\n

The ILR-33 BURSZTYN 2K rocket is a flying suborbital platform designed at \u0141ukasiewicz \u2013 Institute of Aviation. ILR-33 BURSZTYN 2K is offered as a standalone product, as well as a platform that enables research services. Powered by a hybrid rocket engine, supported by two auxiliary engines, it allows the mission to be tailored to the specific needs of the cargo being lifted.<\/p>\n\n

ILR-33 BURSZTYN 2K \u2013 Main advantages<\/h3>\n
    \n
  • The world\u2019s first rocket using H2<\/sub>O2<\/sub> with a concentration exceeding 98%<\/li>\n
  • Innovative hybrid rocket engine<\/li>\n
  • Low cost of suborbital flights<\/li>\n
  • Scalability \u2013 possibility of developing larger rocket systems<\/li>\n<\/ul>\n\n

    Technical data<\/h3>\n\n
    ILR-33 BURSZTYN 2K<\/strong><\/td><\/tr>\n
    Length<\/td>4.6 m<\/td><\/tr>\n
    Main stage diameter<\/td>230 mm<\/td><\/tr>\n
    Flight ceiling<\/td>100 km<\/td><\/tr>\n
    Maximum speed<\/td>1300 m\/s<\/td><\/tr>\n
    Payload weight<\/td>10 kg<\/td><\/tr>\n
    Maximum gravity load<\/td>14 g<\/td><\/tr>\n
    Duration of microgravity (10-3<\/sup> g, 5 kg)<\/td>150 s<\/td><\/tr>\n<\/table>\n\n\n
    Auxiliary engines<\/strong><\/td><\/tr>\n
    Type<\/td>Solid propellant<\/td><\/tr>\n
    Maximum thrust<\/td>2 \u00d7 16,000 N<\/td><\/tr>\n
    Working time<\/td>6 s<\/td><\/tr>\n
    Combustion chamber<\/td>Composite structure<\/td><\/tr>\n<\/table>\n\n\n
    Main engine<\/strong><\/td><\/tr>\n
    Type<\/td>Hybrid rocket engine<\/td><\/tr>\n
    Oxidizer<\/td>Hydrogen peroxide (H2<\/sub>O2<\/sub>), concentration 98%+<\/td><\/tr>\n
    Fuel<\/td>Polyethylene<\/td><\/tr>\n
    Maximum thrust<\/td>4,000 N<\/td><\/tr>\n
    Working time<\/td>40 s<\/td><\/tr>\n
    Combustion chamber<\/td>Composite structure<\/td><\/tr>\n<\/table>\n\n

    Examples of applications<\/h3>\n
      \n
    • Tests in microgravity (200 s after 10-2<\/sup> g)<\/li>\n
    • Validation of avionic systems<\/li>\n
    • Verification of control systems<\/li>\n
    • Qualification of satellites<\/li>\n
    • Tests of separation mechanism of auxiliary engines<\/li>\n
    • Atmospheric sounding<\/li>\n
    • Imitator of ballistic air targets<\/li>\n
    • Ground infrastructure tests<\/li>\n<\/ul>\n\n

      Suborbital flights<\/h3>\n

      The main objective of the ILR-33 BURSZTYN 2K rocket project is to validate key technologies developed for use in modern suborbital platforms, satellites and small carrier rockets. The BURSZTYN rocket is also a cost-effective, scalable and ecological construction, enabling efficient experimentation in microgravity and atmospheric probing. It can provide up to 150 seconds of microgravity conditions for a 10 kg payload. The basic version of the rocket has been successfully tested in flight. The payload compartment can be adapted to the Customer\u2019s requirements, providing the best possible test conditions.<\/p>\n\n

      Rocket technologies \u2013 engineering services<\/h3>\n

      Our portfolio includes satellite equipment used in orbit, as well as numerous suborbital rockets \u2013 military and civilian. Striving for engineering excellence and supporting global sustainable development, we are open to both domestic and international cooperation. Thanks to a wide range of services in the area of designing and optimizing solutions for aviation and space, the services we offer contribute to the development of new technologies.<\/p>\n

        \n
      • Designing vehicles and drives:\n
          \n
        • Solid, hybrid and liquid rocket propulsion<\/li>\n
        • Mechanisms, valves, bearings<\/li>\n
        • Composite structures<\/li>\n
        • Navigation and control systems<\/li>\n
        • On-board computers and other electronic systems<\/li>\n
        • Structural strength (finite element method)<\/li>\n
        • Flow analysis, combustion modeling (finite element method)<\/li>\n
        • Systems engineering<\/li>\n <\/ul>\n <\/li>\n<\/ul>\n
            \n
          • Systems validation and testing:\n
              \n
            • Satellite and rocket propulsion systems<\/li>\n
            • Non-destructive tests<\/li>\n
            • Environmental tests<\/li>\n
            • Material tests \u2013 strength, fatigue, etc.<\/li>\n
            • Chemical tests<\/li>\n <\/ul>\n <\/li>\n<\/ul>\n\n

              Rocket subsystems and components<\/h3>\n

              In addition to our commitment to propulsion, our engineers have developed key subsystems for rockets and satellites. The acquired knowledge enables the design of components in terms of even the most demanding assumptions.<\/p>\n\n

              Pyrotechnic devices<\/h4>\n
                \n
              • Pyrotechnic cutters<\/li>\n
              • Linear hollow charges<\/li>\n
              • Pyrovalves<\/li>\n
              • Igniters<\/li>\n
              • Actuators<\/li>\n
              • Pushers<\/li>\n
              • Mortars<\/li>\n<\/ul>\n\n

                Missile recovery systems<\/h4>\n
                  \n
                • Parachute systems<\/li>\n
                • Wind tunnel testing<\/li>\n
                • Use of the flat spin phenomenon<\/li>\n
                • Drop tests<\/li>\n
                • Simulations<\/li>\n
                • Sea surface recovery system<\/li>\n<\/ul>\n\n

                  Control systems and electronic systems for rockets<\/h4>\n
                    \n
                  • On-board computers<\/li>\n
                  • Launch management systems<\/li>\n
                  • Data acquisition<\/li>\n
                  • Control systems<\/li>\n<\/ul>\n\n

                    Separation mechanisms<\/h4>\n
                      \n
                    • Separation systems for auxiliary engines, separation system for the main rocket member<\/li>\n
                    • Separation methods:\n
                        \n
                      • \u201cFire in the hole\u201d<\/li>\n
                      • Pyrotechnic separation<\/li>\n
                      • Aerodynamic separation<\/li>\n <\/ul>\n <\/li>\n<\/ul>\n\n

                        Avionic rocket control systems<\/h3>\n

                        We are working on avionic equipment for rockets in three areas:<\/p>\n\n

                        Measurements<\/h4>\n

                        We have extensive experience in integrating systems for measuring basic flight parameters such as linear and angular velocities and the spatial position of the rocket. We have used proprietary inertial navigation algorithms, which enable short-term autonomous navigation calculations, in the on-board computers of the rockets we have developed.<\/p>\n\n

                        Control<\/h4>\n

                        We have developed flight control algorithms for rockets made at the Institute of Aviation. In the ILR-33 AMBER 2K rocket, the on-board computer controls the rocket flight by means of coordinated inclination of the control surfaces \u2013 four canards placed symmetrically in the front part of the rocket. In other rockets \u2013 by means of control motors located around the rocket\u2019s hull.<\/p>\n\n

                        Special features<\/h4>\n

                        We have also developed algorithms responsible for the implementation of the assumed flight plan and the electrical initiation of other rocket systems, such as the launch system, separation system or landing part recovery system. The rocket\u2019s on-board computer, designed and built, is an example of this type of solution.<\/p>\n

                        The developed algorithms and control methods are implemented by on-board computers designed, manufactured and tested\t\t\t\t\t\t\t\t<\/div>\n\t\t\t\t<\/div>\n\t\t\t\t\t<\/div>\n\t\t\t\t<\/div>\n\t\t\t\t<\/div>\n\t\t","protected":false},"excerpt":{"rendered":"

                        Home Strona With the ILR-33 BURSZTYN 2K rocket, a cost-effective, scalable and environmentally friendly design, we have the ability to efficiently experiment in microgravity and probe the atmosphere. The ILR-33 BURSZTYN 2K rocket is used during flight as a suborbital test platform, capable of providing up to 150 seconds of microgravity conditions for a 10 […]<\/p>\n","protected":false},"author":230,"featured_media":0,"parent":106165,"menu_order":0,"comment_status":"closed","ping_status":"closed","template":"","meta":{"_acf_changed":false,"_seopress_robots_primary_cat":"","_seopress_titles_title":"","_seopress_titles_desc":"","_seopress_robots_index":"","inline_featured_image":false,"footnotes":""},"class_list":["post-106170","page","type-page","status-publish","hentry"],"acf":{"czas_czytania":"3","wyroznij":"0"},"publishpress_future_action":{"enabled":false,"date":"2026-05-13 11:31:22","action":"change-status","newStatus":"draft","terms":[],"taxonomy":"translation_priority","extraData":[]},"publishpress_future_workflow_manual_trigger":{"enabledWorkflows":[]},"_links":{"self":[{"href":"https:\/\/ilot.lukasiewicz.gov.pl\/en\/wp-json\/wp\/v2\/pages\/106170","targetHints":{"allow":["GET"]}}],"collection":[{"href":"https:\/\/ilot.lukasiewicz.gov.pl\/en\/wp-json\/wp\/v2\/pages"}],"about":[{"href":"https:\/\/ilot.lukasiewicz.gov.pl\/en\/wp-json\/wp\/v2\/types\/page"}],"author":[{"embeddable":true,"href":"https:\/\/ilot.lukasiewicz.gov.pl\/en\/wp-json\/wp\/v2\/users\/230"}],"replies":[{"embeddable":true,"href":"https:\/\/ilot.lukasiewicz.gov.pl\/en\/wp-json\/wp\/v2\/comments?post=106170"}],"version-history":[{"count":4,"href":"https:\/\/ilot.lukasiewicz.gov.pl\/en\/wp-json\/wp\/v2\/pages\/106170\/revisions"}],"predecessor-version":[{"id":106174,"href":"https:\/\/ilot.lukasiewicz.gov.pl\/en\/wp-json\/wp\/v2\/pages\/106170\/revisions\/106174"}],"up":[{"embeddable":true,"href":"https:\/\/ilot.lukasiewicz.gov.pl\/en\/wp-json\/wp\/v2\/pages\/106165"}],"wp:attachment":[{"href":"https:\/\/ilot.lukasiewicz.gov.pl\/en\/wp-json\/wp\/v2\/media?parent=106170"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}