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The differentiation of RES‐models properties as a function of the scalar position of the considered model seems to conform to the following principles: 1. The probability of the presence of a given antinomic state in the property “d” (dynamic) is directly influenced by the position of the model on the size‐scale; 2. The “d” state having been adopted by the RESm‐model, i.e. dmon or dplu, determines the adoption of the state in other mechanical and informational properties in the model under consideration; 3. Each organization of a new model, which is concerned with the RESm‐models series, is accompanied by an inversion of antinomic states in (at least two) cardinal RESm‐properties. Some of the cardinal properties appear as a function of antinomic states inversions during the evolution‐oscillation phenomena of the models.

The placement of each class of self regulating systems on the dimensional scale is a factor which determines the following : type of forces being responsible for the integration of the structural elements of the system; types of channels inside the negative feedback that supports the equilibrium of the internal system; degrees of motion freedom of structural elements inside biosystems can be higher than those of non‐condensed systems; existence of energy transformers (mitochondria) in biosystems and their absence in natural abiotic systems; very high number of specific submodels of the B‐system (living systems).

The paper begins with a description of some cybernetic aspects of Anthropophysics. This is concerned with a formal treatment of man's system under both its possible states: The normal one and the one perturbed by disease, the latter being the object of studies in medicine.

Biophysics is considered as the physics of ultra‐complex systems. “Complexity” is defined on the levels of architecture, structure and form. The paper studies degrees of complexity and preliminary conditions for the organization of complex systems. Examples are given and favorable factors for inauguration of the complexificatory mechanisms enumerated.

An attempt at unification of different groups of physical phenomena by use of cybernetic methodology in order to avoid a dualism in the formalism of Natural Self‐Regulating Systems (NRS) in now being carried out simultaneously by physics and cybernetics. A proposal is made of a unitary elaboration within a framework of cybernetic physics, which should concern not only events belonging to micro‐ and macro‐physics, but also those which are placed intermediately on the size scale, especially systems organized by the biogenesis phenomena and subjected to the laws of a “Meso‐physics”. The systems that result from this evolutively lend themselves to treatment within the framework of an organic branch, which would be a physics of systems endowed with a multihierarchized architecture and ultra‐complex structure.

The purpose of this paper is to present the methodology and approach adapted to conduct a wind tunnel experiment on the inverted joined-wing airplane flying model together with the results obtained.

General assumptions underlying the dual-use model design are presented in this paper. The model was supposed to be used for both wind tunnel tests and flight tests that significantly drive its size and internal structure. Wind tunnel tests results compared with the outcome of computational fluid dynamics (CFD) were used to assess airplane flying qualities before the maiden flight was performed.

Extensive data about the aerodynamic characteristics of the airplane were collected. Clean configurations in symmetric and asymmetric cases and also configurations with various control surface deflections were tested.

The data obtained experimentally made it possible to predict the performance and stability properties of the unconventional airplane and to draw conclusions on improvements in further designs of this configuration.

The airplane described in this paper differs from frequently analyzed joined-wing configurations, as it boasts a front lifting surface attached at the top of the fuselage, whereas the aft one is attached at the bottom. The testing technique involving the application of a dual-use model is also innovative.

The global economy is facing a steep challenge from volatility, risk and uncertainty associated with climate change, pandemics, regional conflicts and trade wars which are unprecedented and overlapping. These crises are leading to macro- and microeconomic imbalances. The immediate effects like rising inflation, shortage of energy and fertiliser, food insecurity, loss of jobs and poverty are looming large, leading to existential threat. It is evident that decades of progress are at risk and pursuing sustainable development goals (SDGs) requires dedicated and customised efforts by the governments and other relevant actors, especially in the low- and middle-income countries (LMICS). The concept of circular economy is considered to bring a paradigm shift by reducing the dependence on natural resource extraction and decoupling economic growth from use of natural resources. Bioeconomy is another emerging field which deals with the use of renewable biological resources such as biomass to produce renewable biofuels, bioproducts, and biopower for economic, environmental and social benefits. Circular bioeconomy (CBE) lies at the intersection and is defined as the production of recoverable biological (waste) resources and the conversion of these resources into high-value-added products, such as food, feed, bio-based products and bioenergy. It has been estimated that the economic opportunity for the sector to complement or even substitute conventional ones is estimated to be USD 7.7 trillion by 2030 for food and feed waste products, and energy. CBE is perceived as a pathway for development and has the potential to target different SDGs directly like 6, 7 and 12 and SDGs 2, 3, 11, 12, 13 and 15 indirectly. This study explores the linkages of CBE with the SDG goals and provides recommendations to stimulate the sector.

The epigallocatechin gallate (EGCG) effect in diabetes has been investigated in animal studies, but results of clinical trials are inconsistent. Thus, this study aims to evaluate the effects of EGCG supplementation in patients with type 2 diabetes mellitus (T2DM).

A total of 50 patients with T2DM were recruited in a double-blind, randomized, placebo-controlled trial. The eligible participants were randomly allocated to EGCG (n = 25) and placebo (n = 25) groups. The EGCG group received two capsules of EGCG (each capsule contained 150 mg; Shari Made®, Iran) and placebo group was administered two capsules of placebo (starch) for eight weeks. A three-day 24-h dietary recall and anthropometric and laboratory measurements were carried out at the beginning and the end of the study.

At the end of the trial, weight and body mass index (BMI) were decreased significantly in both groups, but the reduction was not statistically significant between the two groups. Fasting blood sugar decreased significantly in EGCG group. No significant between-group and within-group differences were found in insulin, homeostatic model assessment of insulin resistance (HOMA-IR) and the quantitative insulin sensitivity check index values. The high-sensitive C-reactive protein (hs-CRP) was significantly reduced in the EGCG group (4.13 ± 0.48-3.93 ± 0.50, p = 0.003) compared to baseline.

This study showed that consuming 300 mg/day of EGCG for eight weeks in patients with T2DM caused a significant decrease in fasting blood glucose, body weight, BMI and hs-CRP compared to baseline. Therefore, the EGCG supplementation may improve glycemic control, anthropometric and inflammation status in T2DM.

According to the study of the space flight market, there is a demand for space suborbital flights including commercial tourist flights. However, one of the challenges is to design a mission and a vehicle that could offer flights with relatively low G-loads. The project of the rocket-plane in a strake-wing configuration was undertaken to check if such a design could meet the FAA recommendation for this kind of flight. The project concept assumes that the rocket plane is released from a slowly flying carrier plane, then climbs above 100 kilometers above sea level and returns in a glide flight using a vortex lift generated by the strake-wing configuration. Such a mission has to include a flight transition during the release and return phases which might not be comfortable for passengers. Verification if FAA recommendation is fulfilled during these transition maneuvers was the purpose of this study.

The project was focused on the numerical investigation of a possibility to perform transition maneuvers mentioned above in a passenger-friendly way. The numerical simulations of a full-scale rocket-plane were performed using the simulation and dynamic stability analyzer (SDSA) software package. The influence of an elevator deflection change on flight parameters was investigated in two cases: a transition from the steep descent at high angles of attack to the level glide just after rocket-plane release from the carrier and an analogous transition after re-entry to the atmosphere. In particular, G-loads and G-rates were analyzed.

As a result, it was found that the values of these parameters satisfied the specific requirements during the separation and transition from a steep descent to gliding. They would be acceptable for an average passenger.

To verify the modeling approach, a flight test campaign was performed. During the experiment, a rocket-plane scaled model was released from the RC model helicopter. The rocket-plane model was geometrically similar only. Froude scales were not applied because they would cause excessive technical complications. Therefore, a separate simulation of the experiment with the application of the scaled model was performed in the SDSA software package. Results of this simulation appeared to be comparable to flight test results so it can be concluded that results for the full-scale rocket-plane simulation are also realistic.

It was proven that the rocket-plane in a strake-wing configuration could meet the FAA recommendation concerning G-loads and G rates during suborbital flight. Moreover, it was proven that the SDSA software package could be applied successfully to simulate flight characteristics of airplanes flying at angles of attack not only lower than stall angles but also greater than stall angles.

The application of rocket-planes in a strake-wing configuration could make suborbital tourist flights more popular, thus facilitating the development of manned space flights and contributing to their cost reduction. That is why it was so important to prove that they could meet the FAA recommendation for this kind of service.

The original design of the rocket plane was analyzed. It is equipped with an optimized strake wing and is controlled with oblique, all moving, wingtip plates. Its post-stall flight characteristics were simulated with the application of the SDSA software package which was previously validated only for angles of attack smaller than stall angle. Therefore, experimental validation was necessary. However, because of excessive technical problems caused by the application of Froude scales it was not possible to perform a conventional test with a dynamically scaled model. Therefore, the geometrically scaled model was built and flight tested. Then a separate simulation of the experiment with the application of this model was performed. Results of this separate simulation were compared with the results of the flight test. This comparison allowed to draw the conclusion on the applicability of the SDSA software for post-stall analyzes and, indirectly, on the applicability of the proposed rocket-plane for tourist suborbital flights. This approach to the experimental verification of numerical simulations is quite unique. Finally, a quite original method of the model launching during flight test experiment was applied.