0169

[Zulema Estabrooks]

MT0169 is a second generation engineered toxin body (ETB) that is a single-chain variable fragment (scFv) with an affinity for CD38, fused to the enzymatically active de-immunized Shiga-like toxin-A subunit (SLTA). MT-0169 specifically binds and kills CD38 expressing cells consistent with SLTA mediated cellular cytotoxicity.

MT-0169 is designed to avoid competition with and to overcome the primary mechanisms of tumor resistance to daratumumab. The MT-0169 candidate is active in the presence of daratumumab, which we believe demonstrates its potential to be combined with approved CD38 targeted therapies.

MT-0169 mediates enzymatic and irreversible ribosomal inhibition and induces direct cell death so changes in the tumor microenvironment, such as CD55/59 upregulation, which inhibit immune-mediated mechanisms such as antibody-dependent cell-mediated cytotoxicity (ADCC) or complement-dependent cytotoxicity (CDC) are not expected to inhibit MT-0169 activity.

Dosing was initiated for the Phase 1 clinical trial for MT-0169 in the first quarter of 2020. Although MT-0169 is more potent than our prior program, MT-3724 (our first generation CD20-targeted ETB), it was tolerated at much higher doses than was MT-3724 in non-human primates. The protocol for the dose escalation for MT-0169 starts at 50 mcg/kg. The protocol includes once weekly and once every two-week dosing schedules.

Filbur FC-0169 is a compatible alternative pool and hot tub spa replacement for Arctic Spa jacuzzi cartridges. FC-0169 is designed to fit all Arctic Spas hot tub models 2011 and newer and select Coyote Spas.

Given a simplicial object $U$ in $\mathcalC$ we obtain a sequence of objects $U_ n = U([n])$ endowed with the morphisms $d^ n_ j = U(\delta ^ n_ j) : U_ n \to U_n-1$ and $s^ n_ j = U(\sigma ^ n_ j) : U_ n \to U_n + 1$. These morphisms satisfy the opposites of the relations displayed in Lemma 14.2.3, namely

Remark 14.3.3. By abuse of notation we sometimes write $d_ i : U_ n \to U_n - 1$ instead of $d^ n_ i$, and similarly for $s_ i : U_ n \to U_n + 1$. The relations among the morphisms $d^ n_ i$ and $s^ n_ i$ may be expressed as follows:

We get a unique morphism $s^0_0 = U(\sigma ^0_0) : U_0 \to U_1$ and two morphisms $d^1_0 = U(\delta ^1_0)$, and $d^1_1 = U(\delta ^1_1)$ which are morphisms $U_1 \to U_0$. There are two morphisms $s^1_0 = U(\sigma ^1_0)$, $s^1_1 = U(\sigma ^1_1)$ which are morphisms $U_1 \to U_2$. Three morphisms $d^2_0 = U(\delta ^2_0)$, $d^2_1 = U(\delta ^2_1)$, $d^2_2 = U(\delta ^2_2)$ which are morphisms $U_3 \to U_2$. And so on.

Geometrically Example 14.3.5 above is an important example. It tells us that it is a good idea to think of the maps $d^ n_ j : U_ n \to U_n - 1$ as projection maps (forgetting the $j$th component), and to think of the maps $s^ n_ j : U_ n \to U_n + 1$ as diagonal maps (repeating the $j$th coordinate). We will return to this in the sections below.

Lemma 14.3.6. Let $\mathcalC$ be a category. Let $U$ be a simplicial object of $\mathcalC$. Each of the morphisms $s^ n_ i : U_ n \to U_n + 1$ has a left inverse. In particular $s^ n_ i$ is a monomorphism.

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RD-0169 - is a Russian oxygen-methane fueled rocket engine being developed by KBKhA. Liquefied natural gas (methane) is used as fuel, while liquid oxygen is used as an oxidizer. Designed for use in reusable launch vehicles (like Soyuz-7).

The advantages of the configuraton are: ease of use, environmental friendliness, and the possibility of reusable use. It was planned to achieve a thrust of 200 tons. In the standard version, the pressure in the combustion chamber is planned at 175 kgf/cm2.[1] It is being developed on the basis of RD-0162 with an intermediate and smaller version in the form of RD-0177; two modifications are known: RD-0169A (the engine of the first stage of the Soyuz-7) and RD-0169V (a four-chamber engine of the second stage of the Soyuz-7). The chief designer is Viktor Gorokhov.

At the end of October 2017, a series of fire tests of the RD-0162D2A engine, with a thrust of 40 tons took place; a preliminary design for an oxygen-methane engine with a thrust of 85 tons was subsequently[when?] developed.[4] The next stage involves the specification of design documentation for an engine with a thrust of 85 tons, as well as continued preparation of production and the manufacture of power plants for testing individual engine systems.[5]

On September 26, 2019, a contract was posted on the government procurement website for the creation of a methane engine by the Voronezh KBKhA with a targeted completion date of November 15, 2021. According to the technical specifications, the engine was named RD-0177, the thrust should be 85 tf, the sea level specific impulse should be 312 s, and the mass should not exceed 2200 kg.[citation needed]

On August 27, 2020, Igor Arbuzov, General Director of NPO Energomash, told the media that individual elements of the units of the future methane engine had now been tested - a gas generator, a mixing head. Now the company is moving on to work directly on the production of the RD-0177 demonstrator engine, which they aim to manufacture in 2022.[6][needs update]

On December 24, 2021, at the testing complex of the Voronezh Rocket Engine Center, hot fire tests of the standard autonomous ignition system of the reusable oxygen-methane rocket engine RD-0177 were successfully carried out. According to the chief designer of the KBHA, Viktor Gorokhov, the planned test program was exceeded: within one test day, rather than five starts, eight were carried out, during which they confirmed the operability and plausibility of reusable use of the engine ignition system for future use as part of the return stages of launch vehicles.[7]

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