The defence of the country is an important part to maintain their sovereignty. It does matters because the impact of the defence in life and the longevity of the citizens itself. A country required to be able to retain sovereignty, the unity of the region and the safety of the threats and interference from both inside and outside the country. In order to face the threats, defense required for system of national defense [1].

According to the law no 3 years 2002 article 1 2, verse a defence system the state is defence system that is universe involving our citizens, areas and other national resources, as well as prepared early by the government and held in total, integrated directed and continues to enforce, state sovereignty the unity of the region and the safety of the people.

The defense of a region used to prevent a country, managed less provocation, intervention, infiltration, intimidation and invansion of a military force by other countries stability to offended national security or harness the legal using a country [2].

The R-Han 122 B is a consortium-produced ballistic rocket carried out by several strategic industries with each having different roles and tasks. The development of the R-Han rocket was started in 2005 by the Ministry of Research and Technology (Kemenristek) through a consortium with related research and development (R&D) institutions, one of which is the National Space Flight Agency (LAPAN) represented by the Rocket Technology Center (Pustekroket). The development of this rocket was then continued by the Ministry of Defense by cooperating with State-Owned Enterprises (SOEs) such as PT Pindad (Persero), PT Dirgantara Indonesia (Persero), PT Dahana (Persero) and LAPAN as a government R&D institution. The manufacture and development of the R-Han 122 B rocket through a series of activities and various stages in the design of System Engineering [3].

The results of the design system engineering is being produced next needs the tools to measure the technology to control its development as well to reduce the risk of failure. According to the Regulation of the Minister of Research, High Technology and Education Number 42 in 2016, the level of technology preparation means the condition of ripeness or readiness of outcome, research and development of certain technology which is measured in a systematic with the purpose of it to be adopted by the user, either by the government, industry and the community.

Therefore, researchers were interested in conducting analytical research under the title "Analysis of the Technological Requirements of R-Han 122B Ballistic Rocket Weapon System for Indonesian Defense". The purpose of this study is to find out whether the ballistic rocket requirements desired by the Marine Corps are in accordance with the requirements of the R-Han 122 B ballistic rocket, whether the R-Han 122 B ballistic rocket development process is in accordance with the system engineering stages.

The methods used in this study are qualitative through a descriptive approach to analysis. This research aims to review the R-Han 122 B Ballistic Rocket used by the Marine Corps Navy to support Indonesia's defense. 

Descriptive approach to analysis is used to analyse and explore aspects that are the background to Indonesia's interest in the development of the R-Han 122 B ballistic rocket. Data collection is carried out through interviews aimed at relevant stakeholders as well as secondary data collection through literature studies. The process of analysis and validity of data is carried out using triangulation methods and follows the rules of Miles and Hubberman [4].

Place and Time of Research

This research place is at THE LAPAN Bogor Institution, PT. PINDAD Bandung and Mabes Marine Corps TNI AL East Jakarta. These three places are agencies visited to obtain research data through interviews and secondary data related to R-Han 122 B. This research began from the writing of the proposal in August 2020 until the preparation and implementation of the thesis session in February 2021.

Research Subjects and Objects

The research subject is a person or object to be studied, as well as an informant, which means people in the research background whom used to provide information about the situation and conditions of the research background [5]. The subject of this study is the source who was selected using purposive techniques, which is an expert or expert in the field of R-Han 122 B ballistic rockets and Indonesian state defence systems. 

The object of research is a problem researched in order to obtain research data. The object of this research is the requirements of ballistic rocket systems that can be used by the Navy Marine Corps, the process and development of the R-Han 122 B, as well as the level of technological efficiency (TKT) of the R-Han 122 B ballistic rocket.

Overview of Research Objects

The R-Han 122 B ballistic rocket was formed through a consortium of defence rockets conducted under the guidance of the Ministry of Science and Technology, the Ministry of defence and the Ministry of SOEs. In its implementation, it involves several institutions/agencies that each have a role. 

The role of each agency in the development of the R-Han 122 B ballistic rocket is as in Table 1.

Table 1: Role of Agencies in the R-Han 122 B Consortium

Source: LAPAN, 2019

The manufacture of the R-Han 122 B rocket is a continuation of the development of the RHan 122 caliber 122 mm rocket that has been tested in Batu Raja Palembang, South Sumatra in 2010 whose trajectory capability is about 14 km, because the rocket motor is only 1 (one) meter. For the R-Han 122 B rocket, this development is carried out by increasing the length of the rocket motor to 2 (two) meters so that the trajectory can reach 25 km, which is in accordance with the wishes of the Al army with a minimum range of 20 km. The R-Han 122 B Rocket Launcher Vehicle is a domestically made Multiple Rocket Launcher System (MRLS) by the nation's children. It is expected that the rocket launch process will automatically be able to be executed faster. The rocket-to-launcher charging mechanism is designed in such a way as to achieve a shorter operating time. The launcher system uses the WAGO 750-8206/040-000 XTR Programmable Logic Controller (PLC) as the main controller that can be programmed to store a series of instructions that perform specific functions such as: logic, sequence, timing, counting and arithmetic.

Ballistic Rocket Requirements Used by the Navy's Marine Corps

During this time the Marine Corps used ballistic rockets made by the Cekoslowakia Army Ecxalibur, the RM-70 Grad. The technical specifications of the RM-70 Grad are as in Table 2.

Table 2: Technical Specifications of RM-70 Grad

Source: Ministry of Defence, 2019

Gap Analysis on Ballistic Rocket Requirements

Differences in technical specifications on the requirements of the R-Han 122 B ballistic rocket with the RM-70 Grad are a contributing factor to the gap in the ballistic rocket's capabilities at the time of use. Researchers found that differences in the fuel (propellant) used as well as the level of precision (flight stability) provide gaps as presented in Table 3.

Table 3: Causal Factors and Gaps Caused

Source: Research Institute, 2021

Fuel Factor (Propellant)

The R-Han 122 B uses A&E HTPB composite base propellant, while the RM-70 Grad uses a double base solid propellant. This makes the R-Han 122 B still emit thick smoke at the time of launch. The double base propellant consists of nitro-glycerine NG and nitrocycline NC as its binders.

The R-Han 122 B uses HTPB composite propellant. The cause of smoke in the remaining combustion of propellant because this propellant belongs to a heterogeneous type of propellant that has differences in material and structure in composite solid propellant, namely the composition of propellant with fuel and oxidizer that is mixed but has no bond between the two or called non uniform structure. Because it has no bond, the building material of this propellant is bound with a binder that usually has a polymer hydrocarbon structure such as HTPB.

The composite propellant in R-Han 122 B is based on Ammonium perchlorate which normally produces white smoke at the time of combustion. This is because one of the results of burning HCl nucleated condensation of water vapor in the atmosphere, resulting in fog [6]. The smoke is not produced if nitrates are used but decreases performance due to a reduction in specific impulses. Ammonium perchlorate-HTPB is the most commonly used combination because HTPB is considered a superior binding material for achieving high combustion performance as well as the desired physical and mechanical properties of propellant. Azide polymers such as GAP and BAMO are also used with Ammonium perchlorate or nitrates to formulate composite propellants. The addition of metal fuels such as Al allows for a significant increase in the temperature of the adiabatic flame of composite propellants. When aluminium is used, combustion products contain large amounts of aluminium oxide (Al2O3) in the chamber, most of which are in the liquid phase.

Precision Capability Factor (Flight Stability)

In terms of precision capability (flight stability), related to the level of consistency of the direction of the rocket at the time of launch, namely whether the rocket launched can fall collect (grouping) about the target or not. There are several factors that affect the ideal condition of flight stability.

The first factor that affects precision or flight stability is the thrust (N) profile. Rockets work by converting heat power into kinetic energy. The heat arising from the combustion process in the combustion chamber of the rocket motor. In this process produces gases that are high temperature and accumulate in the combustion chamber and cause combustion pressure. The gas is a radiated gas that comes out through the high speed. In accordance with Newton Ill's law, the result of the speed of the radiative gas resulted in the onset of thrust in the opposite direction to the direction of the gas emission. The greater the speed of the gas emission out of the nozzle will result in greater thrust produced. The speed of the radiated gas that comes out of the nozzle is influenced by many factors including the type of fuel, combustion temperature, combustion pressure and the area of the exophages nozzle.

The second factor that affects the ability of precision or flight stability is the dimensions of geometry. One of the things that influences the dimensions of geometry on the ability of rockets to fly is the costs and symmetry at the time of the installation of fins or fins against the main axis on the rocket, thus affecting the magnitude of drag that occurs when the rocket flies, this affects the performance of flying that impacts the lack of precision of the rocket or grouping [7]. A good rocket is to have a straight and symmetrical geometric dimension design. In addition, the fin design must also be made as small as possible so as not to exert a major influence that inhibits the rocket during flight.

The third factor that affects precision or flight stability capability is CG or centre of graphite which affects wobbling movement (non-linear conus movement) that sometimes occurs in ballistic rocket flight tests [8]. The position of the centre of graphite or the centre of mass of the rocket that is not on the axis symmetry of the rocket occurs due to the distribution of the mass of the rocket that is not symmetrical. Imperfections in design and manufacturing, the physical condition of the materials used and the placement of poorly designed rocket components. When the position of the centre of graphite or the centre of the rocket mass is not located on the axis symmetry of the rocket can result in disruption of the moment roll, pitch and yaw on the rocket that triggers wobbling movement [9]. Therefore, the R-Han 122 B ballistic rocket needs static-dynamic balancing before being tested to fly in order to know the centre of graphite or the centre of mass of the rocket whether it is on the axis symmetrical axis or not.

The fourth factor that affects precision or flight stability is the atmosphere. In the rocket's dynamic test activities, the atmospheric has an effect of 3% to cause test failure. It is affected by changes in direction and wind speed in detail in the atmosphere. The R-Han 122 B test was equipped with the provision of wind data forecasting information and measurements directly using radiosonde. Radiosonde observations show detailed information about changes in direction and wind speed that affect the results of the rocket's dynamic test and the preparation of a firing table [10]. The results of radiosonde measurements can also be used by PSTA researchers to validate the results of WRF models and research related to atmospheric boundary layers.

User Needs Analysis Stage

According to the Navy Marine Corps, the requirements that must be met in ballistic rockets are as follows:

• Rocket ammunition must be flexible to the firing range so that it can support fire assistance since the manoeuvre is still on the shoreline to seize the outermost target of the beach pedestal as far as 50 km

• There are rocket munitions with a range of more than 100 km to destroy the parent body of the opposing amphibious combat group before developing manoeuvres

• Rocket ammunition must be safe for its own forces both technically and tactically

• As a free rocket, the accuracy and consistency of rocket ammunition must be meticulous and can be calculated with certainty adjustments to weather conditions

• Can use several kinds of projectiles/ammunition according to the calibre of rockets such as he grenades, frag grenades, smoke grenades, cargo grenades, fill grenades, etc.

The development of the R-Han 122 B rocket that is a user requirement (Marine Corps TNI AL) is close to the specifications of the Technical Standard (SST) of the RM-70 Grad rocket, which is expected to be mass produced as well as meet the munition of the MARINE CORPS ARTILLERY RM-70 Grad Rocket [11]. The R-Han 122 B rocket is only focused on the creation of firing tables, namely the retrieval of parameter data, validation of target data and distance or trajectory and the characteristics that can be known with certainty, before being mass produced and used by the Navy Marine Artillery. The development of R-Han 122 B is done by increasing the length of the rocket motor to 2 (two) meters so that the trajectory can reach 25 km, in accordance with the wishes of the Al army with a minimum reach distance of 20 km. In the R-Han 122 B certificate number IMAA TC AW/Rocket 001-2019, there is no document requirement about the specifications of R-Han ballistic rockets desired by the Marine Corps TNI AL. Thus, it is not yet known what kind of technical specifications of the ballistic rocket desired by the user.

Fabrication Process Stage

Fabrication is a creative process of forming metal materials into a desired rocket form in accordance with design standards and shop drawing that has been made. At this stage, the production process is carried out on a small scale. Starting from 20-25 units conducted to meet the production trial stage of R-Han 122 B.

This fabrication phase starts from the purchase of materials and raw materials or rocket components needed in the development of R-Han 122 B. The purchase of such components was made to Korea. In 2019 in addition to the development of R-Han122 B rockets produced by conventional (semi free standing) methods, there has also been the development of R-Han 122 B rockets produced with case-bonded methods, using hanwha Korean production line facilities. This stage of implementation begins with the formulation of propellant and liner until the appropriate formulation is found based on the results of test characteristics, both for mechanical characteristics and ballistic characteristics.

When it has entered the integration stage, there is integration between ballistic rocket components [12]. Where the components that have been purchased are combined and integrated into a single unit that can be continued with the production process into the finished product. At this stage of integration is evidenced by the Rocket Integration Check List with the number R-HAN.122B-024 on June 24, 2018.

Based on the results of research and discussions that have been outlined, it can be concluded that the R-Han 122 B the results of the consortium development have not been in accordance with the ballistic rocket desired by the Marine Corps navy because there are differences in terms of requirements. That's the type of propellant used. The R-Han 122 B propellant uses an HTPB composite, causing thick smoke. While the ballistic rocket used by the Navy Marine Corps (RM 70 Grad) uses a double base solid propellant so that the smoke generated is thin. At the precision capability (flight stability) the launch of R-Han 122 B has not been collected (grouping). The development of the R-Han 122 B ballistic rocket has not followed the system engineering stage fully. This is because there is no document user requirement at the user needs analysis stage.

As a recommendation, if the R-Han 122 B ballistic rocket will be developed and adapted to the needs of users/Marine Corps navy, then it should be made changes to the type of propellant that uses double base solid propellant so that the residual combustion smoke becomes thin. In addition, it is necessary to increase the capability of fligt stability so that when the rocket is launched can be grouping and all development must follow the stages of system engineering.

1. Muhaimin, Y.A. Pointy Bamboo and Gunpowder: Defense Development Problems in Indonesia. Yogyakarta: Graha Knowledge, 2014.

2. Ministry of Defense. Indonesian Defense White Paper. Jakarta: Ministry of Defense of the Republic of Indonesia, 2015.

3. Herjuna, D. Conceptual Design of Marine Multiple Launch Rocket System Rocket Artillery System. Bogor: Indonesian Defense University, 2019.

4. Cresswell, J.W. Research Design: Qualitative, Quantitative and Mixed (Translation) Approaches. Yogyakarta: Student Library, 2016.

5. Moleong, L.J. Qualitative Research Methods. Bandung: Teen Works, 2011.

6. Arip, S. and H.A. Luthfia. “Propellant and Manufacturing Techniques.” Aerospace News, vol. 15, no. 2, 2014, pp. 50-57.

7. Atmadi, S. “Effect of Irregularity and Symmetry of Fin Installation on RX-250-LPN Rocket Flying Performance.” Journal of Aerospace Technology, vol. 1, no. 2, 2010, pp. 1-9.

8. Hoult. “Rocket Principles.” Rocket: A Teacher’s Guide with Activities in Science. Journal of Mathematics and Technology, vol. 8, no. 2, 2015, pp. 99-108.

9. Karthikeyan, T.V. and A.K. Kapoor. Guided Missiles. Delhi: Ministry of Defense, 1990.

10. LAPAN. Pustekroket Performance Accountability Report 2019. Bogor: LAPAN, 2020.

11. Yakti, P.D. The Navy as a World Class Navy on Defense Strategy in Realizing the World Maritime Axis. Semarang: Diponegoro University, 2017.

12. Nugraha, H. et al. “Analysis of Medium-Range Missile System Requirement Air Defense System for National Vital Object Security (Kosekhanudnasi Case Study).” Journal of Defense, vol. 1, no. 3, 2020, pp. 16-32.